US Pat. No. 9,334,741

DISCREETLY DEFINED POROUS WALL STRUCTURE FOR TRANSPIRATIONAL COOLING

Siemens Energy, Inc., Or...

1. A porous structure comprising:
a wall comprising an interior and an exterior surface;
a pattern of discretely defined voids in the wall forming a plurality of serpentine passages effective to provide transpiration
cooling between the interior and exterior surfaces;

wherein the serpentine passages are formed by partially overlapping voids in alternating layers of the wall;
and wherein the layers are non-parallel to a plane of the interior or exterior surface.

US Pat. No. 9,058,520

SYSTEMS AND METHODS FOR HANDS FREE INSPECTION

Siemens Corporation, Ise...

11. A system to inspect a turbine with an inspection computer and a camera, comprising:
a wireless mobile device, enabled to establish wireless connectivity with the inspection computer, wherein the wireless mobile
device includes a processor enabled to execute instructions to perform the steps:

selecting a stream of interest of images of the turbine and a region of interest within the stream of interest;
requesting the stream of interest and the region of interest from the inspection computer and then receiving images representing
the region of interest in the stream of interest from the inspection computer;

displaying the region of interest on a display;
sending a request to the inspection computer for a model of the turbine in a region of interest and for an image of the turbine
in the region of interest;

receiving the model of the turbine and the image of the turbine in the region of interest from the inspection computer; and
displaying the model of the turbine and the image of the turbine in the region of interest on the wireless mobile device.

US Pat. No. 9,488,618

GENERATOR RETAINING RING AND OTHER COMPONENT THERMAL DEGRADATION EVALUATION BY EDDY CURRENT NON-DESTRUCTIVE EXAMINATION

Siemens Energy, Inc., Or...

1. A method for non-destructive evaluation of one or more of yield strength, toughness, or tensile ductility physical properties
of monolithic material forming a generator retaining ring, which property is altered by temperature change in the material
that results from thermal exposure of the ring, comprising:
providing a generator ring constructed of a monolithic, solid metal material;
measuring the provided generator ring's International Annealed Copper Standard (IACS) electrical conductivity with an eddy
current test system, at a single test frequency;

obtaining reference data sets for test samples of the same monolithic, solid metal material, which are generated by:
heating separate, plural, respective test samples, of the same monolithic material, to respective desired different temperatures
for a common exposure period, and thereafter allowing each sample to cool to ambient temperature,

measuring, for each respective cooled test sample, its IACS electrical conductivity, at the same single frequency, and one
or more of its yield strength, toughness or tensile ductility physical properties;

comparing the provided generator ring's measured IACS electrical conductivity to the reference data set's measured IACS conductivities
of the test samples, and

deriving, for the provided generator ring, one or more of its yield strength, toughness or tensile ductility physical properties
or its prior thermal exposure temperature, based on its measured electrical conductivity and corresponding electrical conductivity/physical
property information in the reference data set; and

evaluating whether at least one of the provided generator ring's yield strength, toughness or tensile ductility physical properties,
which is derived from the test data set, is acceptable for use in a generator.

US Pat. No. 9,325,388

WIRELESS TELEMETRY SYSTEM INCLUDING AN INDUCTION POWER SYSTEM

SIEMENS ENERGY, INC., Or...

1. A telemetry system for use in a combustion turbine engine having a compressor, a combustor and a turbine, the telemetry
system comprising:
a sensor on a turbine blade;
a telemetry transmitter circuit affixed to the turbine blade;
a first electrical connection on the turbine blade for routing electronic data signals from the sensor to the telemetry transmitter
circuit, the electronic data signals indicative of a condition of the turbine blade;

an induction power system for powering the telemetry transmitter circuit comprising:
at least one stationary primary induction coil assembly affixed to a stationary component adjacent to the turbine blade; and,
a rotating secondary induction coil assembly mounted to an end face of a root of the turbine blade;
wherein the stationary primary induction coil assembly comprises a plurality of ceramic substrates, including a first and
last ceramic substrate, mounted to a static seal segment of the stationary component and the ceramic substrates are aligned
end to end forming a
continuous arc spanning a circumference of the static seal segment wherein on each ceramic substrate a planar winding is formed
and the planar windings are electrically connected in series to adjacent planar windings on adjacent ceramic substrates, and
an external power source is electrically connected to the planar winding of the first ceramic substrate and to the planar
winding of the last ceramic substrate in the series;
a rotating data antenna affixed to the end face of the root of the turbine blade;
a second electrical connection on the turbine blade for routing the electronic data signals from the telemetry transmitter
circuit to the rotating data antenna; and,

a stationary data antenna affixed to the stationary component.

US Pat. No. 9,273,562

PROJECTION RESISTANCE WELDING OF SUPERALLOYS

Siemens Energy, Inc., Or...

1. A method for joining superalloy structures, comprising:
forming a recess in a superalloy component substrate having a recess profile defined by the remaining substrate;
forming a mating superalloy splice having a splice projection, with a projection profile conforming with the substrate recess
profile along a corresponding mutual contact surface;

inserting and capturing the splice within the recess, so that the projection and recess are in abutting contact along the
contact surface;

compressing the substrate and splice projection together along the contact surface at a selected pressure;
conductively contacting the substrate and splice with separate electric resistance welding electrodes;
applying selected compression pressure and passing current at a selected flow rate and application time period through the
substrate and splice projection between the electrodes until localized melting occurs along the contact surface, ejecting
a volume of localized melted material out of the mutual contact surface that avoids, or crack-inducing shrinkage stresses
or solidification cracking during post-weld cooling, ceasing further current flow after the substrate and splice projection
are mutually affixed to each other along the contact surface and;

wherein the recess and splice projection conforming profiles form an outwardly diverging gap for initiating melting proximate
a narrower portion of the gap, and for promoting melt front formation and ejection outwardly towards a wider portion of the
gap and out of the recess during said ejecting;

avoiding, after cessation of current flow, crack-inducing shrinkage stresses or solidification cracking during subsequent
contact surface cooling or during post-weld heat treatment.

US Pat. No. 9,272,324

INVESTMENT CASTING PROCESS FOR HOLLOW COMPONENTS

Siemens Energy, Inc., Or...

1. A method of forming a ceramic core for an investment casting process, the method comprising the steps of:
forming a master tool using a machining process to define a first region of the ceramic core;
incorporating an insert into the master tool to define a second region of the ceramic core;
casting a flexible mold in the master tool;
casting ceramic core material into the flexible mold to form the ceramic core; and
removing the flexible mold from the ceramic core while the ceramic core is in a green body state;
further comprising:
heating the green body state core to above a reversion temperature of the ceramic core material after the step of removing;
and

reshaping the green body state core while it is above the reversion temperature.

US Pat. No. 9,133,732

ANTI-ROTATION PIN RETENTION SYSTEM

SIEMENS ENERGY, INC., Or...

1. A turbine engine vane assembly comprising:
a vane;
a shroud ring supporting the vane and comprising an outer surface, an inner surface, and a protrusion formed on the outer
surface, said shroud ring defining an aperture extending from the outer surface to the inner surface;

a cavity seal comprising a cavity outer surface, a cavity inner surface, and a protrusion receiving portion corresponding
to the protrusion of the shroud ring; and

a securement mechanism comprising a shaft having a first end and a second end, said shaft having a first diameter at the first
end and a second diameter at the second end, said first diameter being larger than the second diameter, wherein said shaft
has a diameter between the first end and the second end that is greater than the second diameter and less than the first diameter,
and comprising a key at the second end of the shaft, said securement mechanism adapted for insertion through the aperture,
wherein upon insertion, said key protrudes from the aperture at the cavity inner surface and the inner surface of the shroud
ring,

said securement mechanism being rotatable between a first configuration and a second configuration, wherein in the second
configuration, said key matingly engages the shroud ring such that an outer surface of the key abuts the inner surface of
the shroud ring.

US Pat. No. 9,255,526

SYSTEM AND METHOD FOR ON LINE MONITORING WITHIN A GAS TURBINE COMBUSTOR SECTION

Siemens Energy, Inc., Or...

1. A method for on-line optical operational monitoring of an industrial gas turbine combustion section, comprising:
coupling a man way cover having an optical window to a combustion section service man way;
directing the field of view (FOV) of an optical camera located outside the man way cover through the optical window, so that
the FOV is capable of capturing images of areas of interest within the combustion section;

moving the camera FOV to plural positions within the combustion section and capturing respective images at each position;
and

combining the respective captured images in a composite image
remote vibration monitoring of the areas of interest by monitoring relative motion of the areas of interest and correlating
the motion with vibrational frequency.

US Pat. No. 9,274,027

APPARATUS AND PROCESS FOR MEASURING THE DEPTH OF A GROOVE IN A ROTOR OF A GAS TURBINE ENGINE

Siemens Energy, Inc., Or...

1. Apparatus for measuring a depth of a groove defined between adjacent steeples of a rotor of a turbine, the groove being
adapted to receive a root of a blade, said apparatus comprising:
a measuring tool comprising:
a fixture; and
first and second depth measuring devices associated with said fixture for measuring the depth of the groove at two spaced
apart locations;

wherein said first and second depth measuring devices are mounted to said fixture and include axially spaced apart measuring
probes, each movable to provide a depth measurement of the groove relative to said fixture at two axially spaced apart locations
along a length of the groove.

US Pat. No. 9,272,369

METHOD FOR AUTOMATED SUPERALLOY LASER CLADDING WITH 3D IMAGING WELD PATH CONTROL

Siemens Energy, Inc., Or...

1. A method for welding turbine components, comprising:
providing a work table, laser profilometer and laser welding apparatus under common control by a control system, for providing
controlled relative motion between the work table and either of the profilometer or welding apparatus;

coupling a turbine component having a substrate to the work table;
scanning a surface of the turbine component substrate in real time by operating the laser profilometer and work table apparatus
under control of the control system and acquiring component dimensional data;

comparing component dimensional data with specification dimensional data in real time with the control system and determining
a welding pattern for building up component substrate surface portions to conform welded component dimensions to the specification
dimensional data; and

welding the component substrate surface in real time by operating the laser welding and work table apparatuses in conformity
with the determined welding pattern under control of the control system.

US Pat. No. 9,137,462

HOUGH TRANSFORM APPROACH TO GAP MEASUREMENT IN BLADE INSPECTION

Siemens Corporation, Ise...

1. A method to measure a width of a gap between two moving parts in a machine, comprising:
recording an image of the gap with an infra-red camera and storing the image as image data, wherein the gap is between two
adjacent blades in a rotating turbine rotor of a gas turbine;

a processor extracting a first and a second edge related to the gap from the image data;
the processor applying a Hough transform to a plurality of pixels of the first edge to determine a first line and to a plurality
of pixels of the second edge to determine a second line, substantially parallel to the first line and applying voting related
to the plurality of pixels of the first edge to select line parameters of pixels in a majority;

the processor applying a line through at least one pre-defined point that crosses the first and second lines;
the processor determining the width of the gap from a length of the line through the at least one pre-defined point that crosses
the first and second lines; and

determining a performance of the gas turbine based on the width of the gap.

US Pat. No. 9,314,883

AUTOMATED CUTTING OF A CYLINDRICAL WORKPIECE

SIEMENS ENERGY, INC., Or...

1. A method for dimensioning a segment of a cylindrical element comprising:
positioning a cutting device against an interior diameter of the segment of the cylindrical element;
activating a motor to rotate the cutting device about an axis to cut the cylindrical element;
cutting the cylindrical element by way of the motor about the axis; and
securing the cutting apparatus to the cylindrical element,
wherein upon activation of the motor, the cutting device is guided along a circumferential direction against the interior
diameter of the segment,

wherein the securing includes attaching a first face plate of the cylindrical element to a second face plate of the cutting
device using a plurality of clamps.

US Pat. No. 9,404,377

TURBINE BLADE AND NON-INTEGRAL PLATFORM WITH PIN ATTACHMENT

SIEMENS ENERGY, INC., Or...

1. A turbine blade and platform apparatus, comprising:
first and second turbine blades, each blade comprising a pressure side, a suction side, and a shank portion, wherein the shank
portion is mounted to a turbine disk; and

a first platform spanning between the pressure side of the first turbine blade and the suction side of the second turbine
blade;

wherein the first platform is non-integral with the turbine blades, is mounted to the turbine disk between the first and second
blades, and comprises:

a first rotationally forward edge portion that overlies a seal element on the pressure side of the first turbine blade and
does not underlie a ledge on the pressure side of the first turbine blade;

a first rotationally rearward edge portion that underlies a shelf on the suction side of the second turbine blade; and
the first platform is configured for radial installation and removal between the mounted first and second turbine blades without
removal of said blades.

US Pat. No. 9,395,126

METHOD AND APPARATUS FOR COOLING SUPERALLOY TURBINE COMPONENTS DURING COMPONENT WELDING

Siemens Energy, Inc., Or...

1. A heat sink apparatus for cooling a superalloy turbine component during component welding, comprising:
a fluid-filled cooling bladder having an outer contact surface, for abutting orientation and enveloping contact with a portion
of a turbine component surface, and an inner surface in communication with the cooling bladder internal, first cooling fluid;

the cooling bladder outer contact surface formed with a non-gaseous, conformable, heat conductive material for conforming,
abutting contact with the turbine component surface; and

a clamping shroud, for enveloping the cooling bladder and the turbine component, so that all of the outer contact surface
is in direct, gap-less contact with the corresponding turbine component surface, and the inner surface is in communication
with the cooling bladder internal, first cooling fluid, the clamping shroud including a flexible, inflatable cuff that creates
a compressive biasing force, for biasing the outer contact surface and the component surface against each other.

US Pat. No. 9,300,172

DONUT STATOR CORE-FRAME ATTACHMENT TECHNIQUE

SIEMENS ENERGY, INC, Orl...

1. A generator comprising:
a frame including a bore and a plurality of circumferentially disposed construction bolts mounted around and extending within
the bore;

a plurality of stacked stator packs defining a stator core, each stator pack including a plurality of circumferentially disposed
notches around an outer perimeter of the stator pack that align with notches in the other stator packs and form slots extending
the length of the stator core, each notch including opposing side walls where one of the side walls is shaped to conform to
the construction bolt in a mating engagement and the other sidewall includes a groove; and

a plurality of wedge sets for mounting the stator packs to the construction bolts, each wedge set including a solid filler
piece configured to be positioned within the groove and a construction bolt filler piece having a shaped portion that conforms
to the construction bolt, said wedge set further including a wedge piece positioned between the filler pieces and forcing
the filler pieces apart to secure the stator packs to the construction bolt, wherein a single wedge set is provided within
each notch.

US Pat. No. 9,127,551

TURBINE COMBUSTION SYSTEM COOLING SCOOP

Siemens Energy, Inc., Or...

1. A cooling apparatus that redirects a coolant fluid, comprising;
a transition duct wall disposed in a coolant flow in a can-annular gas turbine engine;
a plurality of scoops disposed over a respective plurality of coolant inlet holes formed in the transition duct wall at locations
upstream of a region defining a minimum distance between the transition duct wall and an adjacent transition duct wall, each
scoop comprising a leading edge with a central projection that overhangs the respective coolant inlet hole and an undercut
on each side of the central projection between the central projection and a base of the scoop attached to the transition duct
wall; and

a plurality of partial scoops disposed over a respective plurality of coolant inlet holes formed in the transition duct wall
at locations downstream of the region defining the minimum distance between the transition duct wall and the adjacent transition
duct wall, each partial scoop comprising a generally planar leading edge lying in a plane leaning rearward from a leading
end of the attachment base to form an acute angle with a plane of the transition duct wall proximate the respective coolant
inlet hole.

US Pat. No. 9,470,102

CRACK RESISTANT TURBINE VANE AND METHOD FOR VANE CONTAINMENT CAP ATTACHMENT

Siemens Energy, Inc., Or...

1. A stress-crack resistant gas turbine vane, comprising:
an inner shroud having an inboard surface and an outer surface;
a vane containment cap having a rim surface in opposed spaced orientation above the inboard surface, defining a root gap between
the rim and inboard surfaces, and an outer face adjacent the rim surface, the outer face being offset from and noncoplanar
to the outer surface of the inner shroud;

the rim and inboard surfaces welded to each other by a penetrating flat weld filler formed in and filling the root gap, and
an intact, semi-circular profile bead weld filler outboard the penetrating weld filler, joining the containment cap outer
face and the inboard surface on an exposed exterior of the turbine vane; and

the flat weld filler allowing inner shroud and vane containment cap relative flexure, while resisting formation of stress
riser cracks in the semi-circular profile bead weld filler, and the bead weld filler resisting formation of, or subsequent
propagation of, separation stress cracks in the flat weld filler.

US Pat. No. 9,354,190

APPARATUS AND METHOD FOR MONITORING AND QUANTIFYING PROGRESSION OF A STRUCTURAL ANOMALY IN A HIGH TEMPERATURE ENVIRONMENT OF A COMBUSTION TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. Apparatus for monitoring and quantifying progression of a structural anomaly over a surface of a component in a high temperature
environment of a combustion turbine engine, the apparatus comprising an electrically-insulating layer formed at least over
a portion of the surface of the component of said combustion turbine engine; and at least a first detection leg disposed on
the electrically-insulating layer, wherein the first detection leg is configured to operate under a desired sensing modality
from a bi-modal sensing scheme available for monitoring and quantifying the progression of the structural anomaly.

US Pat. No. 9,255,522

MODULAR DROP-IN TRANSITION ASSEMBLY FOR INDUSTRIAL GAS TURBINE AND METHOD FOR INSTALLATION

Siemens Energy, Inc., Or...

7. An installation system for an industrial gas turbine engine transition assembly, comprising:
an assembled industrial gas turbine engine having coupled compressor, combustor, and turbine sections, the combustor section
including a combustor case having a combustor access port for receipt of a transition therein that is coaxially aligned therewith
along a transition insertion path;

a preassembled, drop-in transition assembly having a mounting flange adapted for slidable coupling with a combustor basket
once the transition assembly is inserted into the combustor access port;

a combustor service zone surrounding the assembled gas turbine engine, for facilitating slidable insertion of the transition
assembly into the combustor access port along the transition insertion path without contacting other gas turbine engine external
or internal components, the combustor service zone having axial depth at least between the combustor section combustor access
port and the compressor section, as well as vertical height and lateral width at least as large as corresponding height and
width of the combustor case;

a powered transition handling tool (THT), for slidably inserting the transition assembly into the combustor access port along
the transition insertion path, the THT confined within the combustor service zone during transition assembly insertion, the
THT including:

a vertical support column anchored outboard the combustor case within the combustor service zone axial depth;
a lifting platform, coupled to the vertical support column, for selectively varying vertical elevation within combustor service
zone;

a transition gripper, for coupling to the transition assembly;
a transition alignment platform, coupled to the lifting platform and the transition gripper, the transition alignment platform
including,

a first slider set for providing selective linear translation of the transition gripper orthogonally with respect to the vertical
support column in a lateral width direction within the combustor service zone;

a second slider set for providing selective linear translation of the transition gripper orthogonally with respect to the
vertical support column in an axial depth direction within the combustor service zone;

a first turret assembly for providing selective tilting inclination/declination of the transition gripper within the combustor
service zone;

a second turret assembly for providing selective sweep/pan pivoting movements of the transition gripper within the combustor
service zone; and

a drive system for driving the lifting platform and the transition alignment platform elevation, translation and pivoting
motions during transition assembly insertion along the transition insertion path.

US Pat. No. 9,255,835

SYSTEM FOR REMOTE VIBRATION DETECTION ON COMBUSTOR BASKET AND TRANSITION IN GAS TURBINES

Siemens Energy, Inc., Or...

1. A method for sensing combustion-induced vibration characteristics in a gas turbine engine combustor, comprising:
providing an operating gas turbine engine, which includes a combustor having a combustor housing, which defines an interior
including therein combustor basket and transition components that entrain combustion gasses, and an inspection port in communication
with the housing interior that is accessible from outside the housing, the inspection port including therein at least one
optical pipe or optical window for preventing combustion gas escape from the housing interior;

providing a non-contact reflective optical vibration sensor in optical communication with the respective inspection port optical
pipe or window and the respective combustor basket or transition components, the sensor having a photon source and photon
detector oriented outside the combustor housing;

providing a vibration analyzer coupled to the non-contact reflective optical vibration sensor that correlates photons received
by the photon detector with vibration frequency and/or magnitude characteristics;

providing a gas turbine engine monitoring system, coupled to the vibration analyzer, the monitoring system capable of associating
vibration characteristics sensed by the sensor with operating engine vibration characteristics that are indicative of combustion
gas flame front position or a flameout condition;

reflecting photons off of an exterior circumferential surface of the combustor basket or the transition component within the
operating combustor with the photon source;

receiving reflected photons with the photon detector
correlating, with the vibration analyzer and the monitoring system, photons received by the detector with vibration characteristics
of the corresponding combustor basket or transition component and identifying operating engine combustion gas flame front
position or a flameout condition therewith.

US Pat. No. 9,257,873

METHOD AND APPARATUS FOR GENERATOR STATOR CORE SEPARATION

Siemens Energy, Inc., Or...

1. A method for separating an intercoupled assembled stator core from a non-vertically oriented generator frame, comprising:
providing a generator, which includes an assembled stator core having a lamina stack of individual laminations that are retained
in compressed axial and radial alignment by an opposed pair of stator core end plates and axially oriented bolts that are
coupled to the respective end plates; a generator frame that circumscribes the assembled stator core; and coupling members
for coupling the assembled stator core and frame;

decoupling respective coupled stator core and frame coupling members;
interposing at least one sliding member between the stator core and frame; and
sliding the respective assembled stator core and frame relative to each other on the at least one sliding member, without
removing individual laminations from the assembled stator core lamina stack, so that they are separated from their initially
coupled relative positions.

US Pat. No. 9,470,147

APPARATUS AND METHOD FOR DETERMINING A TEMPERATURE DISTRIBUTION OF A HOT-TEMPERATURE FLOW IN A TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. A method comprising:
locating a grid in a path of a hot-temperature flow between a combustor and a first expansion stage of a turbine section in
a turbine engine;

sensing infrared emissions from the grid over a period of time of operation of the turbine engine;
determining a two-dimensional temperature distribution in a cross-sectional path of the flow based on the sensed infrared
emissions; and

configuring the grid to oxidize and harmlessly disperse in the hot-temperature flow over the period of time of operation of
the turbine engine so that the grid is absent between the combustor and the first expansion stage of the turbine section during
subsequent operation of the turbine engine.

US Pat. No. 9,446,480

REINFORCED CLADDING

SIEMENS ENERGY, INC., Or...

1. A method comprising:
forming a melt pool comprising a superalloy material and a plurality of discrete carbon reinforcing structures on a superalloy
substrate via application of energy from an energy source; and

cooling the melt pool to form a reinforced cladding comprising the superalloy material and the carbon reinforcing structures
on the substrate.

US Pat. No. 9,353,949

DEVICE FOR IMPROVED AIR AND FUEL DISTRIBUTION TO A COMBUSTOR

SIEMENS ENERGY, INC., Or...

6. A flow conditioning device for a can annular gas turbine engine, comprising:
a plurality of annular plates disposed in a compressed air flow path leading to a combustor and adjacent one another along
a direction of flow, wherein each of the plurality of annular plates has a top surface, a bottom surface and a perimeter,
wherein each of the plurality of annular plates comprises at least one opening through the top surface and bottom surface;
wherein the at least one opening of each of the plurality of annular plates are associated with each other to establish at
least one flow conditioning path through the plurality of annular plates; and

wherein rotation about a common axis of one plate with respect to another adjusts a hydraulic diameter of the least one flow
conditioning path during operation of the can annular gas turbine engine.

US Pat. No. 9,350,319

SELF-POWERED SENSING AND TRANSMITTING DEVICE AND METHOD OF FABRICATING THE SAME

SIEMENS ENERGY, INC., Or...

1. A self-powered sensing and transmitting circuit, comprising:
a power element;
a sensing element powered by the power element for generating a sensor signal responsive to a local operating environment;
a transmitting element powered by the power element for transmitting an output signal responsive to the sensor signal to a
receiving location remote from the circuit; and

wherein the power element, sensing element and transmitting element are arranged in a generally planar and non-integrated
circuit configuration and formed on a substrate component configured to operate at temperatures at or exceeding 650° C.

US Pat. No. 9,328,028

STRUCTURE AND METHOD FOR PROTECTING A HYBRID CERAMIC STRUCTURE FROM MOISTURE ATTACK IN A HIGH TEMPERATURE ENVIRONMENT

SIEMENS ENERGY, INC., Or...

1. A hybrid ceramic structure for use in a high temperature combustion environment containing moisture, the structure comprising:
a ceramic matrix composite (CMC) substrate;
a thermal insulation material disposed on the substrate,
the CMC substrate and the thermal insulation material comprising respective materials susceptible to recession when subjected
to temperatures of approximately 1,500° C. and higher in a combustion environment containing moisture and having respective
subsurface cracks or fractures which are inaccessible from respective outward surfaces of the hybrid ceramic structure; and

a coating of water vapor resistant material on respective inner surfaces of at least some of the cracks or fractures in the
CMC substrate to form respective moisture-resistant layers onto the respective inner surfaces of said at least some of the
cracks or fractures as the hybrid ceramic structure transitions from a bisque condition to a fully fired condition.

US Pat. No. 9,216,451

METHOD OF CASTING A COMPONENT HAVING INTERIOR PASSAGEWAYS

Mikro Systems, Inc., Cha...

18. A method comprising:
forming a plurality of sheets of fugitive material, each sheet corresponding to a respective layer of a desired three dimensional
structure, each sheet defining a respective plurality of void areas;

stacking the plurality of sheets to form the three dimensional structure, the plurality of void areas in predetermined adjacent
sheets being aligned to define respective portions of a plurality of convoluted passageways within the three dimensional structure,
wherein the three dimensional structure comprises an outer perimeter defining a fugitive mold die;

injecting ceramic material slurry into the three dimensional structure and allowing the ceramic material to harden, wherein
the ceramic material slurry forms an outer ceramic shell at the outer perimeter of the three dimensional structure, the forming
of the outer ceramic shell in the fugitive mold die effective to eliminate a lost wax process in connection with the forming
of the outer ceramic shell;

removing the fugitive material from the hardened ceramic material to reveal a cast ceramic component;
prior to removing the fugitive material, providing an external shell structure that substantially surrounds the three dimensional
structure, the external shell structure and the cast ceramic component together forming a casting vessel for receiving molten
alloy material after removal of the fugitive material;

injecting the molten alloy material into the cast ceramic component and allowing the alloy material to harden, the shape of
the plurality of convoluted passageways thereby being reproduced in the alloy material; and

removing the cast ceramic component from the hardened alloy material to reveal a cast alloy component having a plurality of
convoluted interior passageways.

US Pat. No. 9,551,227

COMPONENT COOLING CHANNEL

Mikro Systems, Inc., Cha...

1. A cooling channel in a component, the cooling channel comprising: a first near-wall inner surface aligned substantially
parallel to a first exterior surface of the component; a first plurality of substantially parallel fins, located on the first
near-wall inner surface, that are substantially longitudinally aligned with a flow direction of the cooling channel; wherein:
the first plurality of substantially parallel fins comprises a height profile that is convex across a width of the first near-wall
inner surface as viewed in a transverse section plane of the cooling channel, wherein the transverse section plane is normal
to the flow direction; and a maximum height of the height profile varies along a length of the cooling channel.

US Pat. No. 9,453,784

NON-INTRUSIVE MEASUREMENT OF HOT GAS TEMPERATURE IN A GAS TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. A method of operating a gas turbine engine, including determining a temperature of a working gas passing through a flow
path within the gas turbine engine, the method comprising the steps of:
transmitting an acoustic signal from an acoustic transmitter located at a predetermined axial location along the flow path
of the gas turbine engine;

receiving the acoustic signal from the acoustic transmitter at an acoustic receiver located at the predetermined axial location;
the acoustic signal being encoded with a distinct signature defined by a set of predetermined frequencies transmitted as a
non-broadband acoustic signal;

wherein receiving the acoustic signal includes comparing a received signal to one or more transmitted signals to identify
a similarity of the received signal to a transmitted signal to identify a transmission time for the received signal;

determining a time-of-flight for the signal from the acoustic transmitter to the acoustic receiver; and
processing the time-of-flight for the signal to determine a temperature in a region of the predetermined axial location.

US Pat. No. 9,440,287

COATINGS FOR HIGH TEMPERATURE COMPONENTS

SIEMENS ENERGY, INC., Or...

1. A method of coating a substrate comprising:
to an assembly comprising a substrate, a porous matrix on the substrate, and an impregnating material on or within the porous
matrix, applying an amount of energy from an energy source effective to melt the impregnating material and a portion of the
substrate such that the impregnating material impregnates the porous matrix; and

cooling the assembly to provide a coating comprising the impregnated porous matrix integrated with the substrate;
wherein the porous matrix comprises a material having a higher melting temperature than that of the impregnating material.

US Pat. No. 9,393,644

CLADDING OF ALLOYS USING FLUX AND METAL POWDER CORED FEED MATERIAL

SIEMENS ENERGY, INC., Or...

1. A method comprising:
providing a feed material comprising a sheath consisting essentially of pure nickel containing a powdered core material, the
powdered core material comprising powdered metal material and powdered flux material;

melting the feed material onto a substrate to form a melt pool;
allowing the melt pool to cool to form a layer of clad material of a desired composition covered by a layer of slag; further
comprising:

selecting the powdered metal and powdered flux materials to comprise elements that complement the sheath to form the clad
material as a desired superalloy material when melted onto the substrate; and

selecting the sheath and powdered core materials such that the clad material desired composition is a superalloy composition
that lies beyond a zone of weldability when displayed on a graph of superalloys plotting titanium content verses aluminum
content, wherein the zone of weldability is upper bounded by a line intersecting the titanium content axis at 6 wt. % and
intersecting the aluminum content axis at 3 wt. %.

US Pat. No. 9,358,643

METHOD FOR BUILDING A GAS TURBINE ENGINE COMPONENT

SIEMENS ENERGY, INC., Or...

1. A method, comprising:
providing a layer of powder material on a hollow substrate comprising pressure side skin, suction side skin, a rib connecting
the pressure side skin to the suction side skin, and protruding rib material protruding from the rib and past the suction
and pressure side skins; and

traversing an energy beam across the layer of powder material to form a cladding layer around and bonded to the protruding
rib material, wherein the cladding layer defines a layer of an airfoil skin.

US Pat. No. 9,470,422

GAS TURBINE STRUCTURAL MOUNTING ARRANGEMENT BETWEEN COMBUSTION GAS DUCT ANNULAR CHAMBER AND TURBINE VANE CARRIER

Siemens Energy, Inc., Or...

1. A gas turbine engine ducting arrangement, comprising: a ducting arrangement comprising a plurality of discrete ducts, each
duct disposed between a respective combustor can and an annular chamber, the annular chamber configured to receive a combustion
gas flow from each of the plurality of discrete ducts and to deliver the combustions gas flows to a turbine inlet annulus;
an outer diameter mounting arrangement at a location radially outward of the annular chamber with respect to a central axis
of the annular chamber configured to permit relative radial movement and to prevent relative axial movement between an outer
wall of the annular chamber and a turbine vane carrier; and

an inner diameter mounting arrangement comprising a bracket secured to the turbine vane carrier at a location radially outward
of the annular chamber with respect to the central axis of the annular chamber, discrete from the outer diameter mounting
arrangement, and in a way that permits relative radial movement and prevents relative axial movement between an inner wall
of the annular chamber and the turbine vane carrier, wherein the bracket is configured as a cantilever support with radial
freedom for the inner wall.

US Pat. No. 9,388,704

VANE ARRAY WITH ONE OR MORE NON-INTEGRAL PLATFORMS

Siemens Energy, Inc., Or...

1. A vane array adapted to be coupled to a vane carrier within a gas turbine engine comprising:
a plurality of elongated airfoils comprising at least a first airfoil and a second airfoil located adjacent to one another;
a U-ring;
first connector structure for coupling a radially inner end section of each of the first and second airfoils to said U-ring;
second connector structure for coupling a radially outer end section of each of the first and second airfoils to said vane
carrier;

a first platform extending between said first and second airfoils and positioned near said radially inner end sections of
the first and second airfoils;

a second platform extending between said first and second airfoils and positioned near said radially outer end sections of
the first and second airfoils;

third connector structure for coupling said first platform to said U-ring; and
fourth connector structure for coupling said second platform to said vane carrier.

US Pat. No. 9,352,413

DEPOSITION OF SUPERALLOYS USING POWDERED FLUX AND METAL

SIEMENS ENERGY, INC., Or...

9. A method comprising:
covering a portion of a surface of a superalloy substrate with a layer of powder consisting essentially of flux material and
superalloy metal material;

melting the powder with an energy beam applied to the layer of powder at room temperature to create a melt pool and floating
slag; and

allowing the melt pool to cool and solidify under the slag to form a repaired surface of a desired superalloy material.

US Pat. No. 9,352,419

LASER RE-MELT REPAIR OF SUPERALLOYS USING FLUX

SIEMENS ENERGY, INC., Or...

1. A method comprising:
applying powdered flux material to a surface of a superalloy substrate containing a surface opening defect;
traversing an energy beam across the surface to form a re-melted zone in the substrate covered by an overlying slag layer
without previously performing any subsurface crack cleaning step; and

allowing the re-melted zone to solidify under the slag layer to form a repaired surface free of the defect.

US Pat. No. 9,322,335

GAS TURBINE COMBUSTOR EXIT PIECE WITH HINGED CONNECTIONS

SIEMENS ENERGY, INC., Or...

1. An exit piece for conducting combustion gas from a combustor to a first stage of turbine blades of a gas turbine engine,
the exit piece comprising:
an inlet portion; and
an outlet portion comprising a circumferentially upstream end and a circumferentially downstream end relative to a direction
of rotation of a rotor shaft about an engine centerline;

wherein each circumferential end of the outlet portion comprises a radially inner hinge part and a radially outer hinge part
relative to the engine centerline; and

wherein each of the hinge parts is configured to directly hingedly connect to a mating hinge part on a respective adjacent
outlet portion of an adjacent exit piece when assembled in the gas turbine engine.

US Pat. No. 9,217,852

SYSTEM AND METHOD FOR ONLINE INSPECTION OF TURBINES USING AN OPTICAL TUBE WITH BROADSPECTRUM MIRRORS

Siemens Energy, Inc., Or...

1. A turbine visual image inspection apparatus comprising:
an optical tube housing having a viewing port; and
a visual image reflective mirror array within the optical tube housing in optical alignment with the viewing port, having
a concave objective mirror for capturing an optical visual image within its objective field of view and a convex focal mirror
for focusing the captured image on a focal plane, the mirrors having spectral reflectivity from 550 nm to 20 ?m, and capable
of continuous operation at temperatures greater than 932 degrees Fahrenheit (500 degrees Celsius).

US Pat. No. 9,186,724

ELECTROSLAG AND ELECTROGAS REPAIR OF SUPERALLOY COMPONENTS

Siemens Energy, Inc., Or...

12. A method for repairing a superalloy component, comprising:
providing a superalloy base substrate turbine blade or turbine vane, and a selectively variable temperature mold that defines
a cavity therein, the cavity having a profile with axial height and radial planform circumference dimensions;

placing the base substrate in communication with the mold cavity;
inserting a superalloy metallic electrode and flux in the mold cavity;
coupling the electrode and substrate electrically in series to a current source of a resistance heating apparatus;
passing and regulating a current flow between the electrode and substrate for creating an electroslag layer that covers a
molten metal pool within the mold cavity, which molten metal is in contact with the substrate;

inducing, within the mold cavity, in a growth direction extending upwardly from the substrate, growth of a solidified substrate
extension having a unidirectional-crystalline structure parallel to the cavity axial height dimension, by selectively varying
mold temperature by cooling the mold above the molten metal pool, so that a temperature gradient induced within the substrate
extension is also parallel to the cavity axial height dimension, and thereafter solidifying unidirectionally the molten metal
with the base substrate, thereby creating the substrate extension; and

growing the substrate extension in conformity with the mold cavity profile as the molten metal solidifies.

US Pat. No. 9,133,767

FUEL INJECTING ASSEMBLY FOR GAS TURBINE ENGINE INCLUDING COOLING GAP BETWEEN SUPPLY STRUCTURES

SIEMENS ENERGY, INC, Orl...

1. A fuel injecting assembly comprising:
a gas supply structure for injecting gas fuel, said gas supply structure having a base section including a gas annular manifold
and at least one gas inlet, an intermediate section and an end section having at least one gas outlet, said gas supply structure
defining a passage extending from said at least one gas inlet to said at least one gas outlet;

a steam supply structure for injecting steam, said steam supply structure having a base portion including a steam annular
manifold and at least one steam inlet, an intermediate portion and an end portion having at least one steam outlet, said steam
supply structure defining a passageway extending from said at least one steam inlet to said at least one steam outlet;

an oil fuel nozzle having a base part including at least one oil inlet, an intermediate part and an end part having at least
one oil outlet, said oil fuel nozzle defining a path extending from said at least one oil inlet to said at least one oil outlet,

wherein said gas supply structure, said steam supply structure and said oil fuel nozzle are joined only at said gas supply
structure base section, said steam supply structure base portion and said oil fuel nozzle base part such that said gas supply
structure end section, said steam supply structure end portion and said oil fuel nozzle end part are free to move independently
of one another in an axial direction as said gas supply structure, said steam supply structure and said oil fuel nozzle thermally
expand and contract; and

a first cooling gap adapted to receive cooling air from a first cooling air inlet, wherein a portion of said first cooling
air inlet is at least partially located between a pathway of said gas annular manifold and a pathway of said steam annular
manifold.

US Pat. No. 9,431,864

APPARATUS TO SUPPORT SUPERCONDUCTING WINDINGS IN A ROTOR OF AN ELECTROMOTIVE MACHINE

SIEMENS ENERGY, INC., Or...

1. An apparatus to support at least one superconductor winding in a spaced-apart relationship from a rotor core of an electromotive
machine, the apparatus comprising:
at least one elongated loop arranged to provide radial support to said at least one superconducting winding, the elongated
loop comprising a material substantially resistant to heat flow;

an axially-extending base assembly arranged to anchor said at least one loop with respect to the rotor core at a proximate
end of the elongated loop; and

an assembly having a recess to receive at least a portion of said at least one superconductor winding and to support the elongated
loop at a distal end of the elongated loop.

US Pat. No. 9,358,635

RASTERED LASER MELTING OF A CURVED SURFACE PATH WITH UNIFORM POWER DENSITY DISTRIBUTION

SIEMENS ENERGY, INC., Or...

16. A method comprising:
defining a curved progression path for a melt front on a material surface;
defining a sequence of transverse laser scan lines across the progression path that are each aligned within less than 10 degrees
to a radius of curvature of the progression path, wherein the sequence of scan lines progresses along the progression path;

directing an energy beam along each of the scan lines in succession;
wherein at least some of the scan lines have different respective lengths, forming a scan line pattern that provides a surface
power density of the energy beam that is uniform within a difference of less than 10% between each two bands in a plurality
of equal-width area bands equally dividing a width of the progression path;

wherein the energy beam, by following the pattern, creates the melt front elongated transverse to the curved progression path
and progressing thereon while maintaining said uniformity of the surface power density along a length of the melt front.

US Pat. No. 9,254,537

PLURAL LAYER PUTTY-POWDER/SLURRY APPLICATION METHOD FOR SUPERALLOY COMPONENT CRACK VACUUM FURNACE HEALING

Siemens Energy, Inc., Or...

22. A method for repairing a crack in a vane in a gas turbine engine, said crack including a cavity having a wide top portion
that is wide enough to accept a superalloy putty and a narrow bottom portion that is not wide enough to accept the superalloy
putty, said method comprising:
depositing a superalloy powder slurry in the crack so that the superalloy powder slurry at least partially fills the narrow
bottom portion of the crack;

depositing a superalloy putty layer on top of the superalloy powder slurry to fill the wide top portion of the crack where
the superalloy putty has a higher viscosity than the superalloy powder slurry; and

depositing a braze putty layer on top of the superalloy putty layer.

US Pat. No. 9,658,192

INSULATION DEFECT DETECTION OF HIGH VOLTAGE GENERATOR STATOR CORE

Siemens Corporation, Ise...

1. A method for detecting an insulation defect in a generator core, comprising:
flowing an alternating excitation current at a first excitation frequency through an excitation winding adjacent the generator
core to induce first eddy currents between laminations at the defect;

measuring a first potentiometer voltage indicating magnetic flux caused by the first eddy currents induced at the first excitation
frequency;

flowing an alternating excitation current at a second excitation frequency through the excitation winding adjacent the generator
core to induce second eddy currents between the laminations at the defect;

measuring a second potentiometer voltage indicating magnetic flux caused by the second eddy currents induced at the second
excitation frequency; and

determining a severity of the defect and a depth of the defect using a response voltage relationship among the potentiometer
voltages, the excitation frequencies, the severity of the defect, and the depth of the defect,

wherein the response voltage relationship comprises fitting parameters and a term wherein the excitation frequency is raised
to a function of a fitting parameter.

US Pat. No. 9,134,029

RADIAL MIDFRAME BAFFLE FOR CAN-ANNULAR COMBUSTOR ARRANGEMENT HAVING TANGENTIALLY ORIENTED COMBUSTOR CANS

SIEMENS ENERGY, INC., Or...

1. A can-annular gas turbine engine combustion arrangement, comprising:
a plurality of combustor cans, each comprising a combustor inlet and a combustor outlet circumferentially and axially offset
from the respective combustor inlet;

an outer casing defining a plenum in which the plurality of combustor cans are disposed; and
a plurality of baffles, each baffle of the plurality of baffles oriented to extend radially outward from and axially along
a longitudinal axis of the gas turbine engine, and each baffle reaching the outer casing and the turbine, wherein the plurality
of baffles divide the plenum into sectors, wherein each sector is bound circumferentially by two adjacent baffles and radially
by the outer casing, and wherein each sector defines a respective flow path for compressed air from entry into the plenum
until exiting the plenum, each baffle configured to inhibit circumferential motion of compressed air from one sector to an
adjacent sector.

US Pat. No. 9,297,269

PATTERNED REDUCTION OF SURFACE AREA FOR ABRADABILITY

Siemens Energy, Inc., Or...

1. A gas turbine component comprising:
a substrate;
a layer of ceramic material disposed over the substrate;
a repeating pattern of unconnected cross-shaped depressions formed in the layer of ceramic material defining a continuous
labyrinth of walls of the ceramic material and defining a wear surface, the walls comprising a uniform thickness at the wear
surface separating adjacent depressions;

wherein a representative measurement boundary defines a border of one half of the uniform wall thickness around one of the
cross-shaped depressions;

wherein within the representative measurement boundary along the wear surface, a ratio of a total length of a perimeter of
said one depression divided by an area of the measurement boundary is at least 0.9 per unit of measurement; and

wherein within the measurement boundary the area of said one depression at the wear surface divided by the area of the measurement
boundary is between 0.4 and 0.6.

US Pat. No. 9,114,481

INERTIA FRICTION DISK WELDING

Siemens Energy, Inc, Orl...

1. A method of friction welding comprising,
forming a first cutout in a component, wherein the first cutout comprises a concave surface of rotation that is open radially
to a first edge of the component,

pressing a circumference of a first disk radially into and against the surface of rotation of the first cutout, wherein the
circumference comprises a convex surface that mates with the concave surface of rotation of the first cutout, and

rotating the first disk to create frictional heating that fuses the first disk to the component.

US Pat. No. 9,458,728

METHOD FOR FORMING THREE-DIMENSIONAL ANCHORING STRUCTURES ON A SURFACE BY PROPAGATING ENERGY THROUGH A MULTI-CORE FIBER

SIEMENS ENERGY, INC., Or...

1. A method comprising:
propagating, via a first laser beam, a first laser energy through a first fiber of a multi-core fiber;
propagating, via a non-laser energy source a second non-laser energy selected from one of a mechanical energy, sonic energy,
and ultrasonic energy within a hollow second fiber of the multi-core fiber;

applying the first laser energy to a surface of a substrate to form a liquefied bed on the surface;
applying the second non-laser energy to at least a portion of the liquefied bed to cause a splash of liquefied material outside
the liquefied bed; and

forming on or above the surface of the substrate a three-dimensional anchoring structure upon solidification of the splash
of liquefied material.

US Pat. No. 9,435,212

TURBINE AIRFOIL WITH LATERALLY EXTENDING SNUBBER HAVING INTERNAL COOLING SYSTEM

Siemens Energy, Inc., Or...

1. A turbine airfoil, comprising:
a generally elongated hollow airfoil formed from an outer housing, and having a leading edge, a trailing edge, a pressure
side, a suction side, a root at a first end of the airfoil and a tip at a second end opposite to the first end, and an airfoil
cooling system positioned within interior aspects of the generally elongated hollow airfoil;

a snubber extending from the outer housing forming the generally elongated hollow airfoil toward an adjacent turbine airfoil
positioned within a row of airfoils including the generally elongated hollow airfoil; and

a snubber cooling system positioned within the snubber and formed from at least one inner cooling channel separated from at
least one outer cooling channel by an inner wall, wherein the at least one inner cooling channel is in fluid communication
with the airfoil cooling system via an inlet to receive cooling fluid from the airfoil cooling system within the generally
elongated hollow airfoil and wherein the inner wall includes at least one impingement cooling orifice positioned to allow
cooling fluid to pass from the at least one inner cooling channel and impinge on an inner surface of an outer wall forming
the at least one outer cooling channel.

US Pat. No. 9,420,356

WIRELESS POWER-RECEIVING ASSEMBLY FOR A TELEMETRY SYSTEM IN A HIGH-TEMPERATURE ENVIRONMENT OF A COMBUSTION TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. In a telemetry system in a high-temperature environment of a combustion turbine engine, a wireless power-receiving coil
assembly affixed to a movable component of the turbine engine comprising:
a radio-frequency transparent housing having an opening;
a lid to close the opening of the housing, the lid positioned to provide support against a surface of the movable component;
and

an induction coil assembly comprising a wireless power-receiving induction coil in a substrate, the induction coil assembly
disposed in the housing distally away from the lid and encased between a first layer and a last layer of a potting adhesive
without the induction coil assembly contacting the lid, wherein the lid is arranged to provide vibrational buffering between
the surface of the movable component and the layers encasing the induction coil assembly;

wherein the induction coil comprises at least one planar winding embedded in a ceramic substrate;
wherein the at least one planar winding is connected to electrically power one or more circuitry of the telemetry system located
on the moveable component by way of at least one or more electrical leads arranged to form a loop free of sharp bends between
at least one electrically conductive structure formed on the ceramic substrate and an electrical connector extending through
the housing for electrical connection to the one or more telemetry system circuitry, wherein said at least one electrically
conductive structure on the ceramic substrate is electrically connected to the induction coil.

US Pat. No. 9,341,374

FUEL NOZZLE ASSEMBLY WITH REMOVABLE COMPONENTS

Siemens Energy, Inc., Or...

1. A fuel nozzle assembly for a gas turbine engine comprising:
a rocket unit;
a swirler with an aft end in threaded engagement with a forward end of the rocket unit; and
a clocking feature with a mechanical constraint to orient the swirler at a predetermined angular orientation relative to the
rocket unit;

wherein said clocking feature comprises a flat portion around a circumference of the aft end of the swirler such that upon
engagement of the flat portion with the forward end of the rocket unit, the swirler is oriented at the predetermined angular
orientation.

US Pat. No. 9,328,664

TRANSITION SUPPORT SYSTEM FOR COMBUSTION TRANSITION DUCTS FOR TURBINE ENGINES

SIEMENS ENERGY, INC., Or...

1. An adjustable transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas
turbine inlet of a turbine engine, comprising:
a transition duct body formed from an outer wall that forms an internal passage extending between an inlet and an outlet of
the transition duct body;

an adjustable forward transition flexible support assembly in contact with the transition duct body, wherein the forward transition
flexible support assembly is formed from a base extending toward the transition duct body, and a first side support arm and
a second side support arm extending from the base to the transition duct body;

wherein the first side support arm is formed from a plurality of first side flex plates spaced from each other with spacers,
wherein the first side flex plates provide rigidity in circumferential and radial directions and flexibility in an axial direction;
and

wherein the second side support arm is formed from a plurality of second side flex plates spaced from each other with spacers,
wherein the second side flex plates provide rigidity in circumferential and radial directions and flexibility in the axial
direction.

US Pat. No. 9,597,744

METHOD FOR UTILIZING A BRAZE MATERIAL WITH CARBON STRUCTURES

SIEMENS ENERGY, INC., Or...

1. A method for a brazement with a plurality of carbon structures, comprising:
melting a surface region of a substrate; contacting a braze material with the melted surface region, the braze material comprising
a plurality of braze fillers and the plurality of carbon structures;

subjecting the braze material to an amount of energy effective to melt the braze fillers but not the carbon structures; and
cooling the braze material and melted substrate material of the surface region to form a solidification comprising the carbon
structures nonhomogeneously dispersed within at least a portion of the braze material;

wherein the solidification comprises a gradient of the carbon structures in which a concentration of the carbon structures
within the braze material increases in a direction away from an interior of the substrate.

US Pat. No. 9,316,153

PURGE AND COOLING AIR FOR AN EXHAUST SECTION OF A GAS TURBINE ASSEMBLY

Siemens Energy, Inc., Or...

1. A turbine assembly in a turbine engine, the turbine assembly having an outer casing, an inner casing, an annular exhaust
gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and
radially inward from the gas path, and further comprising:
a plurality of structural struts supporting the inner casing to the outer casing;
a fairing surrounding each of the struts in an area extending between the outer and inner flow path walls;
a first purge air path extending radially inward through at least one of the struts conducting purge cooling air to the inner
casing for supplying purge air to at least one component radially inward from the inner casing; and

a second purge air path extending radially outward through the at least one of the struts for further conducting the purge
cooling air radially outward from the at least one component to provide a flow of purge air to an outer location of the exhaust
casing cavity radially outward from the outer flow path wall.

US Pat. No. 9,206,983

INTERNAL COMBUSTION ENGINE HOT GAS PATH COMPONENT WITH POWDER METALLURGY STRUCTURE

Siemens Energy, Inc., Or...

1. A hot gas path component comprising:
a metallic substrate disposed beneath an outer surface of the component that is exposed to a hot gas present during operation
of an internal combustion engine;

a thermal barrier coating (TBC) layer comprising a TBC first surface in contact with an exterior surface of the metallic substrate
and a TBC second surface defining a first portion of the outer surface of the component;

a powder metallurgy structure comprising a side surface that is coated by the TBC and a bottom surface that is metallurgically
bonded to the exterior surface of the metallic substrate, and

an interlocking geometry between the powder metallurgy structure and the TBC that further secures the powder metallurgy structure
in position, wherein the interlocking geometry is formed by a structure feature extending into the TBC between the TBC second
surface and the metallic substrate.

US Pat. No. 9,188,632

SELF LEARNING RADIO FREQUENCY MONITORING SYSTEM FOR IDENTIFYING AND LOCATING FAULTS IN ELECTRICAL DISTRIBUTION SYSTEMS

Siemens Energy, Inc., Or...

1. A method for monitoring electrical faults in a power plant electrical distribution system, comprising:
monitoring and sampling in real time with an EDS electrical fault monitor (EFM) operation state (OS) radio frequency (RF)
emissions data from electrical distribution system (EDS) equipment that are obtained with a plurality of time synchronized
radio frequency monitors (RFM) that are distributed about the EDS and coupled to the EFM, the OS RF emissions potentially
indicative of electrical faults in the EDS;

storing in an automated data storage device that is coupled to the EFM OS data samples for each RFM, sampled data including
the RFM identification, data sample time and data sample waveform characteristics;

determining with the EFM in real time a likelihood of whether one or a combination of the respective OS data samples is indicative
of an electrical fault by:

referencing in an automated data storage device coupled to the EFM previously stored information associating OS data with
any one or more of EDS safe operation (SO), electrical faults or RF emission location within the EDS;

comparing at least one stored OS sample reading from each RFM with respective stored association information relevant thereto
and making respective EDS safe operation (SO) first confidence level determinations;

comparing a combination of the at least one stored OS sample reading from each respective RFM with respective stored association
information relevant thereto, if such combination information is available, and making respective EDS safe operation (SO)
second or more confidence level determinations; and

combining all prior sequentially determined confidence levels information to derive an EDS safe operation (SO) overall confidence
level; and

causing the EFM to generate an alarm when any of the sequentially determined first through overall SO confidence levels is
indicative of an electrical fault within the EDS.

US Pat. No. 9,291,063

MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH AN IMPROVED ROTATION OF AIR FLOW FROM THE COMPRESSOR TO THE TURBINE

SIEMENS ENERGY, INC., Or...

1. A midframe portion of a gas turbine engine, said midframe portion comprising:
a compressor section with a last stage blade configured to orient an air flow discharged from the compressor section at a
first angle;

a turbine section with a first stage blade configured to receive the air flow oriented at a second angle;
a manifold configured to directly couple the air flow from the compressor section to a combustor head of the gas turbine engine
upstream of the turbine section;

wherein the combustor head is within the manifold and configured to introduce an offset angle in the air flow from the first
angle to the second angle such that the air flow discharged from the combustor head is oriented at the second angle;

and wherein the combustor head is configured to at least maintain or augment the first angle of the air flow.

US Pat. No. 9,283,593

SELECTIVE LASER MELTING / SINTERING USING POWDERED FLUX

Siemens Energy, Inc., Or...

1. A process comprising:
placing a first layer of powder comprising alloy material and flux material on a surface;
indexing an energy beam across the first layer of powder to selectively melt a region of alloy under an overlying layer of
slag;

allowing the alloy and slag to solidify;
removing the slag; and
repeating the placing, indexing and removing steps with a pattern of indexing effective to form a desired component shape;
wherein the alloy material comprises a superalloy composition beyond a zone of weldability defined on a graph of superalloys
plotting titanium content verses aluminum content, wherein the zone of weldability is upper bounded by a line intersecting
the titanium content axis at 6 wt. % and intersecting the aluminum content axis at 3 wt. %; and

wherein the process is performed at an ambient room temperature without preheating the surface, and the slag acts as a blanket
that causes the region of alloy to cool slowly and evenly.

US Pat. No. 9,462,183

TRIGGER FOR BLADE IMAGING BASED ON A CONTROLLER

Siemens Energy, Inc., Or...

1. A method to determine a trigger moment for a controller controlled camera to record an image of a blade attached to a rotating
rotor including a plurality of blades in a turbine, comprising:
the controller controlled camera that is located outside the turbine and pointed at a porthole that provides only a partial
view of a surface of the blade rotating through a field of view of the porthole;

the turbine being operated in an offline condition, wherein the rotating rotor is driven by a motor;
the controller determining a first trigger moment for the camera to capture the blade attached to the rotating rotor based
on a number of the plurality of blades, a preset dwell that determines a part of the blade that is to appear on the image,
a rotating speed of the rotating rotor and a position of the camera outside the turbine, the rotor rotating with a non-uniform
speed within a single period of rotation;

the camera recording and storing on a memory a first image of a first blade in the plurality of blades through the porthole
in the turbine;

the camera recording and storing on the memory a second image of a second blade in the plurality of blades through the porthole
in the turbine;

the controller registering the first and the second image based on a common feature in the first and second blades to determine
a time shift; and

the controller calculating the trigger moment for the blade from the first trigger moment adjusted based on the time shift
to capture the part of the blade in accordance with the preset dwell.

US Pat. No. 9,366,143

COOLING MODULE DESIGN AND METHOD FOR COOLING COMPONENTS OF A GAS TURBINE SYSTEM

Mikro Systems, Inc., Cha...

1. A turbine airfoil comprising:
a root;
a tip;
a pressure side wall;
a suction side wall;
a leading edge connecting the pressure side wall to the suction side wall;
a trailing edge connecting the pressure side wall to the suction side wall;
a first plurality of cooling apertures defined through the trailing edge; and
a cooling arrangement configured to route a cooling fluid from an entrance of the cooling arrangement to an exit of the cooling
arrangement, the exit coinciding with at least one of the first plurality of cooling apertures;

wherein:
the cooling arrangement comprises a first arrangement of serially interconnected flow sections each comprising one or more
chambers, each chamber operatively defining a chamber primary cooling fluid flow direction of a sequence of cooling fluid
flow directions, each chamber primary cooling fluid flow direction selected from:

a radial direction aligned substantially parallel to a path between the root and the tip;
a trailing edge direction substantially parallel to a path between the leading edge and the trailing edge; and
a transverse direction aligned substantially parallel to a path between the suction side wall and the pressure side wall;
the first arrangement of serially interconnected flow sections comprises at least a first flow section, a second flow section,
and a third flow section;

the first arrangement of serially interconnected flow sections is configured to pass the cooling fluid through at least a
portion of the turbine airfoil, and remove heat therefrom;

the first section defines a first plurality of first flow paths extending between the entrance and the second section;
the first section is configured to effect flow of the cooling fluid between the entrance and the second section;
the third section defines a third plurality of third flow paths extending between the second section and the exit, the third
section configured to effect flow of the cooling fluid from the second section and through the third flow paths;

the second section defines one or more second flow paths extending between the first section and the third section, the second
section configured to effect flow of the cooling fluid between the first flow paths and the third flow paths;

the first section is fluidically coupled to said second section solely by one or more first transition chamber;
each first transition chamber defines a corresponding transition flow path that is substantially orthogonal to the first plurality
of first flow paths and that is substantially orthogonal to the one or more second flow paths; and

the number of second flow paths being less than the number of first flow paths.

US Pat. No. 9,293,959

APPARATUS TO SUPPORT SUPERCONDUCTING WINDINGS IN A ROTOR OF AN ELECTOMOTIVE MACHINE

SIEMENS ENERGY, INC., Or...

1. An apparatus to support a superconductor winding in a spaced apart relationship from a rotor core of an electromotive machine,
comprising:
a cradle configured to define a recess to receive the superconductor winding;
at least a first elongated loop and at least a second elongated loop each arranged at a respective angle relative to a radial
axis to provide radial and tangential support to the cradle, wherein the elongated loops comprise a respective material substantially
resistant to heat flow, wherein the cradle is arranged to support said at least first loop and said at least second loop at
respective distal ends of the elongated loops, wherein the elongated loops comprise individual structures; and

an axially-extending base assembly arranged to anchor said at least first loop and said at least second loop with respect
to the rotor core at respective proximate ends of the elongated loops, which proximate ends are respectively located on first
and second mutually opposite sides of the radial axis.

US Pat. No. 9,294,737

FLEXIBLE LINKAGE CAMERA SYSTEM AND METHOD FOR VISUAL INSPECTION OF OFF LINE INDUSTRIAL GAS TURBINES AND OTHER POWER GENERATION MACHINERY

Siemens Energy, Inc., Or...

1. A system for internal inspection of power generation machinery, comprising:
an elongated cable carrier, capable of being maneuvered into internal areas of interest within power generation machinery
from access points outside the machinery, the cable carrier formed from a series of chain links that are pivotally coupled
to each other end-to-end along a series of parallel pivot axes, which parallel axes constrain carrier cable flexure along
a commonly defined carrier cable flexure motion plane, each respective link defining a pair of the of the series of commonly
aligned pivot axes along a link centerline at opposite ends thereof, with adjoining coupled chain links restricted to bi-directional
pivotal motion relative to each link's respective link centerline along the carrier cable flexure motion plane;

a camera head coupled to a distal end of the cable carrier; and
a camera, having a field of view, which is capable of remote image capture, coupled to the camera head.

US Pat. No. 9,234,431

SEAL ASSEMBLY FOR CONTROLLING FLUID FLOW

Siemens Energy, Inc., Or...

1. A seal assembly attached to a first component and in spaced relation to a second component of a machine forming a fluid
flow path therebetween, wherein the first and second components and the seal assembly are subject to high operating temperatures
that cause thermal expansion of the seal assembly and components, the seal assembly comprising:
a first flange end abutting a first surface of the first component;
a second flange end abutting a second surface of the first component that is spaced apart from the first surface; and,
a seal mid-section between and operatively connected to the first and second flange ends;
wherein the first component and first and second flange ends are composed of materials that have substantially the same coefficient
of thermal expansion, and the seal mid-section is composed of a material that has a coefficient thermal expansion that is
different than that of the first component and first and second flange ends; and

the seal mid-section deforms toward the second component when heated towards a steady state operating temperature.

US Pat. No. 9,200,565

FULL HOOP CASING FOR MIDFRAME OF INDUSTRIAL GAS TURBINE ENGINE

Siemens Energy, Inc., Or...

1. A can annular industrial gas turbine engine, comprising:
a single-piece rotor shaft spanning a compressor section, a combustion section, and a turbine section; and
a combustion section outer casing comprising: a first section comprising a single piece annular body configured to connect
to a turbine section casing; a discrete second section disposed between the first section and a compressor section casing;
and an annular joint formed between a radially oriented aftward-facing annular surface of the first section and a radially
oriented forward-facing annular surface of the second section.

US Pat. No. 9,186,740

PROJECTION RESISTANCE BRAZING OF SUPERALLOYS

Siemens Energy, Inc., Or...

1. A method for joining superalloy structures, comprising:
forming a recess in a superalloy component substrate having a recess profile defined by the remaining substrate;
forming a mating superalloy splice having a splice projection, with a projection profile conforming with the substrate recess
profile along a corresponding contact surface;

interposing brazing alloy between the recess and repair splice along the contact surface;
inserting and capturing the splice within the recess, so that the projection and recess are in abutting contact along the
contact surface;

compressing the substrate and splice projection together along the contact surface at a selected pressure;
conductively contacting the substrate and splice with separate electric resistance brazing electrodes; and
passing current at a selected flow rate and application time period through the substrate and splice projection between the
electrodes until brazing alloy melting occurs along the contact surface, and ceasing further current flow after the substrate
and splice projection are mutually affixed to each other.

US Pat. No. 9,444,297

ELECTRICAL CONDUCTORS AND RELATED DEVICES

SIEMENS ENERGY, INC., Or...

1. An electrical machine comprising:
a plurality of electrical conductors for carrying current;
an insulating spacer between adjacent ones of said electrical conductors comprising:
a cured material provided as part of the spacer so that the spacer is the cured material, and
metal portions mixed and immersed within said cured material; and
an electrically insulating banding around the adjacent ones of said electrical conductors and said insulating spacer.

US Pat. No. 9,353,636

PROCESS FOR REPLACING A BOLTED-ON NOZZLE BLOCK COUPLED TO A NOZZLE CHAMBER IN A STEAM TURBINE

SIEMENS ENERGY, INC., Or...

7. A process for replacing a first nozzle block coupled to a nozzle chamber with a second nozzle block comprising:
removing the first nozzle block from the nozzle chamber, the nozzle chamber comprising a main body having at least one inlet,
at least one passage and at least one exit;

coupling inner and outer retaining rings to the nozzle chamber main body;
engaging the second nozzle block with the inner and outer retaining rings so as to couple the second nozzle block to the nozzle
chamber main body;

forming a bore so as to extend partly in one of the inner and outer retaining rings and partly in the second nozzle block;
and

locating an anti-rotation pin in the bore,
machining an outer groove in the nozzle chamber main body and the outer retaining ring and machining an inner groove in the
nozzle chamber main body and the inner retaining ring.

US Pat. No. 9,334,758

STEAM TURBINE MOISTURE REMOVAL SYSTEM

Siemens Energy, Inc., Or...

1. A drain system for connecting to a steam turbine, the drain system comprising:
a main drain line providing a main flow path external to the steam turbine;
a bypass drain line providing a bypass flow path parallel to the main flow path, the bypass flow path external to the steam
turbine;

a drain orifice assembly within the main drain line, the drain orifice assembly accessible during operation of the steam turbine;
and

the main drain line and the bypass drain line configured for connection to a drain path for carrying condensate and contaminants
from the steam turbine;

further comprising a monitoring device for monitoring a condition in the main drain line and for issuing a fault signal responsive
to the condition in the main drain line.

US Pat. No. 9,193,613

PH CONTROL TO ENABLE HOMOGENEOUS CATALYTIC WET AIR OXIDATION

SIEMENS ENERGY, INC., Or...

1. A catalytic wet oxidation process, comprising:
providing an aqueous mixture containing at least one undesirable constituent to be treated;
detecting a pH level of the aqueous mixture containing at least one undesirable constituent to be treated;
selecting a catalyst soluble at the detected pH level of the aqueous mixture, wherein the catalyst and the detected pH level
are selected from the group consisting of: copper at a pH level of about 4 or lower, copper at a pH level above about 13,
vanadium at a pH level above about 4.5, and iron at a pH level below about 4;

contacting the aqueous mixture containing at least one undesirable constituent to be treated with the selected catalyst soluble
at the detected pH level and an oxidizing agent at an elevated temperature and a superatmospheric pressure to treat the at
least one undesirable constituent;

monitoring the pH level of the aqueous mixture; and
maintaining the pH level of the aqueous mixture to maintain the catalyst in a soluble form during the catalytic wet oxidation
process.

US Pat. No. 9,133,721

TURBINE TRANSITION COMPONENT FORMED FROM A TWO SECTION, AIR-COOLED MULTI-LAYER OUTER PANEL FOR USE IN A GAS TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. A transition duct for routing gas flow in a combustion turbine subsystem that includes a first stage blade array having
a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction, said
circumferential direction having a tangential direction component, an axis of the rotor assembly defining a longitudinal direction,
and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of
the first stage blade array, said transition duct, comprising:
a transition duct body having an internal passage extending between an inlet and an outlet:
wherein the duct body is formed at least in part from a multi-panel outer wall; and
wherein the multi-panel outer wall is formed from
an upper section formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum
and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed
between the inner and intermediate panels, and

a lower section formed from an inner panel having an inner surface that defines at least a portion of the hot gas path plenum,
an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between
the inner and intermediate panels and an outer panel positioned radially outward from the intermediate panel;

an attachment system comprising at least one seal body integrally formed with the inner panel of the lower section and having
at least one portion extending radially outward with at least one pocket configured to receive a side edge of the intermediate
panel of the lower section in a sliding arrangement such that the intermediate panel is able to move in-plane relative to
the attachment system and to receive a side edge of the outer panel in a sliding arrangement such that the outer panel is
able to move in-plane relative to the attachment system.

US Pat. No. 9,366,444

FLEXIBLE COMPONENT PROVIDING SEALING CONNECTION

SIEMENS ENERGY, INC., Or...

1. A transition seal assembly for a gas turbine engine, along which exhaust gas generated in a combustion chamber can flow
toward a turbine of the gas turbine engine, the transition seal assembly comprising:
first and second opposing ends with a U-shape body member at the a first end and a seal flange extending along a second end,
the transition seal assembly positionable between a transition section downstream of the combustion chamber and

an inlet flange attached to an inlet section of the turbine, wherein the inlet flange extends circumferentially about an axis
of rotation of the turbine, the seal flange extending away from the first end and along an axial direction defined by the
axis of rotation; and

a flexible member affixed to the transition seal assembly and extending along the seal flange so that, when the transition
seal assembly is positioned between the transition section and the inlet flange of the inlet section, the flexible member
is positioned radially outward from the seal flange with the flexible member comprising a bend making contact with the inlet
flange of the turbine inlet section,

wherein the inlet flange has an inner surface and an outer surface opposite to the inner surface with the inner surface facing
a flow path of the exhaust gas between the transition section and the inlet section and the outer surface faces away from
the flow path, and wherein the flexible member is a spring seal including a first end attached to the transition seal assembly
and a second end opposite to the first end, wherein the second end comprises the bend and wherein the bend comprises a bead
configured to elastically press on the outer surface of the inlet flange such that sealing contact is maintained along a line
of contact between the bead and the outer surface of the inlet flange.

US Pat. No. 9,359,910

METHOD AND APPARATUS FOR MEASURING OPERATIONAL GAS TURBINE ENGINE HOUSING DISPLACEMENT AND TEMPERATURE BY A DISTRIBUTED FIBER OPTIC SENSING SYSTEM UTILIZING OPTICAL FREQUENCY DOMAIN REFLECTOMETRY

SIEMENS ENERGY, INC., Or...

1. A method for measuring operational gas turbine engine housing displacement/temperature, comprising:
coupling a distributed fiber optic sensing system (DFOSS) to a gas turbine engine housing and measuring optical fiber (OF)
temperature influenced strain along the length of the OF by optical frequency domain reflectometry (OFDR) during engine operation;

coupling a temperature sensor to the gas turbine housing and measuring temperature during engine operation;
separating temperature influence from the DFOSS temperature influenced strain measurements with the temperature sensor temperature
measurements and deriving compensated strain measurements; and

correlating the derived strain measurements along the DFOSS with housing displacement of the gas turbine engine.

US Pat. No. 10,340,764

RETIGHTENABLE WEDGE SYSTEM FOR TIGHTENING COIL IN SLOT OF GENERATOR STATOR

SIEMENS ENERGY, INC., Or...

1. A retightenable wedge system for tightening a coil in a slot of a generator stator comprising:a first filler layer placed on the coil;
a spring member placed on the first filler layer;
a second filler layer placed on the spring member;
a retightenable wedge assembly placed on the second filler layer, wherein the retightenable wedge assembly comprises:
a slot wedge comprising an aperture;
a tightening member comprising a form fit feature, wherein the tightening member is configured to be tightenable in the aperture for applying a radial load on the second filler layer, wherein the second filler layer is configured to evenly distribute the radial load on the spring member, and wherein the spring member is configured to apply the evenly distributed radial load onto the coil for tightening the coil in the slot; and
a locking member comprising a mating form fit feature configured to engage with the form fit feature of the tightening member to lock the tightening member in place in the aperture such that the tightening member is able to be restrained from backing out of the slot wedge.

US Pat. No. 9,441,498

PROCESS AND TOOL FOR ALIGNING A SEAL HOUSING ASSEMBLY WITH A CASING OF A GAS TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

4. A process for aligning a seal housing assembly with a casing of a gas turbine engine, the casing comprising a plurality
of connecting portions and the seal housing assembly comprising a plurality of connecting sections, the process comprising:
providing a plurality of adjustment tools, each of the tools comprising:
a main housing including a first bore and a threaded bore,
a first bolt capable of extending through the first bore, and
a second bolt capable of threadedly engaging the threaded bore;
mounting each of the adjustment tools to a corresponding one of the seal housing assembly connecting sections via the corresponding
adjustment tool first bolt;

adjusting the position of the seal housing assembly relative to the casing by causing the second bolt of at least one of the
adjustment tools to rotate so as to apply a force against the casing causing the seal housing assembly to move relative to
the casing,

wherein the first bore comprises a first through bore and each of the adjustment tools further comprises a third bolt capable
of extending through a second through bore in the main housing, said mounting comprises mounting each adjustment tool to a
corresponding one of the seal housing assembly connecting sections via the adjustment tool first and third bolts,

wherein the first and third bolts of each adjustment tool are threadedly received in corresponding threaded bores in the corresponding
one connecting section, and

wherein the main housing of each of the adjusting tools comprises first and second generally planar parts positioned generally
orthogonal to one another, the first and second bores being provided in the first part and the threaded bore being provided
in the second part.

US Pat. No. 9,315,904

MATERIAL DEPOSITION USING POWDER AND FOIL

Siemens Energy, Inc., Or...

1. A method of material deposition comprising:
selecting a powdered metal;
selecting a metal foil comprising a composition and thickness that compensates for a processing loss of an elemental constituent
of the powdered metal during deposition thereof by the method;

disposing both the powdered metal and the metal foil over a surface of a substrate;
melting the powdered metal and metal foil with an energy beam to form a melt pool; and
allowing the melt pool to solidify to form a layer of the deposited material on the substrate surface.

US Pat. No. 9,249,680

TURBINE ABRADABLE LAYER WITH ASYMMETRIC RIDGES OR GROOVES

SIEMENS ENERGY, INC., Or...

1. A turbine abradable component, comprising:
a support surface for coupling to a turbine casing;
a thermally sprayed ceramic/metallic abradable substrate coupled to the support surface, having a substrate surface adapted
for opposed, spaced orientation proximal a rotating turbine blade tip circumferential swept path, with the turbine blade having
a lower pressure side and a higher pressure side; and

at least one asymmetric cross sectional profile ridge projecting from the substrate surface, having an opposed pair of first
and second non parallel lateral walls terminating in a common plateau which extends between the non parallel lateral walls,
the plateau adapted for orientation in opposed spaced relationship with the turbine blade tip, so as to form a blade tip gap
there between.

US Pat. No. 9,206,699

MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH A COOLING SYSTEM FOR THE TRANSITION

Siemens Energy, Inc., Or...

1. A cooling system for a transition duct of a gas turbine engine, comprising:
a cowling configured to receive an air flow from an outlet of a compressor section of the gas turbine engine and configured
to direct the air flow within the cowling in a direction of a rear end of the transition duct; said cowling being positioned
adjacent to a region of the transition duct including the rear end to cool the transition duct region upon circulation of
the air flow within the cowling; and

duct external to the cowling to directly couple the air flow from the compressor section outlet to an inlet of the cowling;
and
wherein said cowling is configured to circulate the air flow around an outer surface of the region of the transition duct.

US Pat. No. 9,188,007

GAS TURBINE SHAFT BEARING SYSTEM SERVICE TOOL AND BEARING SYSTEM SERVICE METHOD

Siemens Energy, Inc., Or...

1. A gas turbine engine bearing system service apparatus for a gas turbine having a rotor shaft and a shaft supporting bearing
system, including a bearing component and a seal component that is slidably mounted on the shaft and captured within a bearing
housing, comprising:
a first member adapted for coupling to a gas turbine rotor shaft;
a second member adapted for coupling to a gas turbine shaft bearing system component;
a biasing force generating unit coupled to the first and second members, for biasing the first and second members relative
to each other so as to slide the bearing system component relative to the shaft;

a hub assembly interposed between the first and second members, with the biasing force generating unit coupled thereto; and
the hub assembly comprising first and second hub plates pivotally coupled to each other along a pivot axis, the first hub
plate coupled to the first member and the second hub plate coupled to the second member, so as to facilitate selective rotational
indexing between the first and second members.

US Pat. No. 9,127,593

MODULAR DROP-IN COMBUSTOR ASSEMBLY FOR INDUSTRIAL GAS TURBINE AND METHOD FOR INSTALLATION

Siemens Energy, Inc., Or...

1. A method for installing a combustor assembly in an assembled industrial gas turbine engine, comprising:
providing an assembled industrial gas turbine engine having coupled compressor, combustor, and turbine sections, the combustor
section including a combustor case having a combustor access port and a transition therein that is coaxially aligned with
the access port along a combustor insertion path;

providing a preassembled modular drop-in combustor assembly having a mounting flange adapted for coupling to the combustor
access port and a combustor basket adapted for slidable coupling with the transition once the combustor assembly is inserted
into the combustor access port and transition along the combustor insertion path;

preparing a combustor service zone surrounding the assembled gas turbine engine, for facilitating slidable insertion of the
combustor assembly into the combustor access port along the combustor insertion path without contacting other gas turbine
engine external or internal components, the combustor service zone having axial depth at least between the combustor section
combustor access port and the compressor section, as well as vertical height and lateral width at least as large as corresponding
height and width of the combustor case;

providing a powered combustor handling tool (CHT), for slidably inserting the combustor assembly into the combustor access
port along the combustor insertion path, the CHT confined within the combustor service zone during combustor assembly insertion,
the CHT including:

a vertical support column anchored outboard the combustor case within the combustor service zone axial depth;
a lifting platform, coupled to the vertical support column, for selectively varying vertical elevation within combustor service
zone;

a combustor gripper, for coupling to the combustor assembly;
a combustor alignment platform, coupled to the lifting platform and the combustor gripper, the combustor alignment platform
including,

a first slider set for providing selective linear translation of the combustor gripper orthogonally with respect to the vertical
support column in a lateral width direction within the combustor service zone;

a second slider set for providing selective linear translation of the combustor gripper orthogonally with respect to the vertical
support column in an axial depth direction within the combustor service zone;

a first turret assembly for providing selective tilting inclination/declination of the combustor gripper within the combustor
service zone;

and a second turret assembly for providing selective sweep/pan pivoting movements of the combustor gripper within the combustor
service zone; and

a drive system for driving the lifting platform and the combustor alignment platform elevation, translation and pivoting motions
during combustor assembly insertion along the combustor insertion path;

coupling the combustor assembly to the combustor gripper;
slidably inserting the combustor assembly into the combustor access port and transition along the insertion path with the
CHT, without contacting other gas turbine engine external or internal turbine components within or outside of the combustor
service zone, while confining the CHT within the combustor service zone during the combustor assembly insertion; and

coupling the combustor assembly mounting flange to the combustor access port.

US Pat. No. 9,096,447

WATER TREATMENT SYSTEM WITH CARBON REGENERATION CIRCUIT

Siemens Energy, Inc., Or...

1. A water treatment system comprising:
a water circuit comprising a source of organic contaminants and a granular activated carbon (GAC)/water contactor for capturing
the organic contaminants; and

a carbon regeneration circuit in fluid communication with the GAC/water contactor for regenerating spent GAC produced in the
GAC/water contactor under wet air regeneration conditions effective to produce regenerated GAC and water comprising dissolved
organics, wherein the water is in a liquid state; and

a fluid path for circulating the liquid water comprising dissolved organics to the water circuit for further treatment,
wherein the fluid path is a fluid path that does not circulate the regenerated GAC back to the water circuit.

US Pat. No. 9,071,096

CLAMPING STRUCTURE FOR A STATOR CORE

Siemens Energy, Inc., Or...

1. A generator comprising:
a frame;
a stator core comprising laminations stacked in said frame;
clamping structure to axially clamp said laminations together comprising:
a plurality of first finger plates positioned adjacent to one another and engaging a first end of said stator core;
a first spacer plate associated with said first finger plates, wherein said first spacer plate is ring-shaped and comprises
a plurality of first recesses circumferentially spaced apart from one another, each of said first recesses having an oval
shape with its longest dimension extending radially;

a plurality of first engagement structures, wherein each of said first engagement structures comprises a bushing capable of
sliding movement relative to said first spacer plate and a bolt in threaded engagement with said bushing;

a first spring ring in engagement with said first engagement structures; and
first load-applying structure coupled to said frame to impart a load to said first spring ring, wherein said spring ring transfers
the load to said stator core via said first engagement structures, said first spacer plate and said first finger plates, said
plurality of first engagement structures being capable of radial movement with said first spring ring and relative to said
first spacer plate as the load is imparted to said first spring ring.

US Pat. No. 9,718,252

PRODUCT WITH INTERNAL PASSAGES MADE OF STACKED SHEETS WITH COMPRESSIVE CASING

SIEMENS ENERGY, INC., Or...

1. A product, comprising:
a stack of sheets, wherein at least some of the sheets have cutouts there through;
the sheets stacked in a predetermined registration that aligns or overlaps at least some of the cutouts in adjacent ones of
the sheets to form internal passages in the stack;

registration pins on a first subset of the sheets;
registration holes in a second subset of the sheets;
wherein the registration pins are in the registration holes, registering the sheets relative to each other; and
an outer casing that spans the stack of sheets and compresses them together.

US Pat. No. 9,683,901

ACOUSTIC MEASUREMENT SYSTEM INCORPORATING A TEMPERATURE CONTROLLED WAVEGUIDE

SIEMENS ENERGY, INC., Or...

1. A measurement system for combustion gas in a gas turbine engine based on propagation of an acoustic signal while the gas
passes through a measurement region in the engine, the system comprising:
a waveguide having first and second ends and a cavity extending between the first and second ends of the waveguide, the first
end configured to adjoin a flow path for injection of the acoustic signal into the measurement region;

an acoustically transmissive physical barrier positioned between a portion of the waveguide and the measurement region to
prevent movement of the combustion gas from the measurement region into the waveguide while permitting transmission of the
acoustic signal from the waveguide into the measurement region; and

a cooling arrangement configured to control an operating temperature of the waveguide
wherein the cooling arrangement further comprises an inlet port and an outlet port extending through a wall defining the cavity
to direct cooling fluid through the cavity, and

wherein the inlet port is configured to direct at least a portion of the cooling fluid onto the acoustically transmissive
barrier.

US Pat. No. 9,453,424

REVERSE BULK FLOW EFFUSION COOLING

SIEMENS ENERGY, INC., Or...

1. A transition component for a gas turbine engine, said gas turbine engine including at least one combustor basket in which
a gas/fuel mixture is combusted to generate a hot working fluid, said transition component comprising a first end mounted
to the combustor basket and receiving the hot working fluid, a second end opposite to the first end outputting the hot working
fluid, and a transition section between the first end and the second end having an outer wall defining a chamber therein through
which the hot working fluid flows, said outer wall having an inside surface and an outside surface, the inside and outside
surfaces being substantially parallel with a direction of a bulk flow, said transition section including a plurality of first
effusion cooling holes extending through the outer wall and being angled in a direction so that an end of the effusion cooling
holes at the inside surface is farther upstream relative to the hot working fluid than an end of the effusion cooling holes
at the outside surface.

US Pat. No. 9,429,546

PHASED ARRAY ULTRASONIC BOLT INSPECTION APPARATUS AND METHOD

Siemens Energy, Inc., Or...

1. An ultrasonic non-destructive evaluation (NDE) inspection apparatus for a fastening bolt, comprising:
a bolt holding fixture adapted for coupling to an end of a bolt about the bolt circumference, for retaining the bolt during
an ultrasonic inspection;

a transducer plate rotatively mounted on the holding fixture, having an axis of rotation aligned with an axial centerline
of a bolt coupled to the holding fixture; and

a phased array ultrasound probe coupled to the transducer plate, having a scanning axis intersecting the bolt circumference
when the bolt is coupled to the holding fixture.

US Pat. No. 9,315,401

WET AIR OXIDATION PROCESS USING RECYCLED COPPER CATALYST

SIEMENS ENERGY, INC., Or...

1. A catalytic wet oxidation system comprising:
a wet oxidation unit;
a source of an aqueous mixture comprising at least one undesirable constituent fluidly connected to the wet oxidation unit;
a source of copper catalyst soluble in the aqueous mixture fluidly connected to the aqueous mixture, the aqueous mixture desired
to have a solubility pH at which the catalyst is substantially soluble, the solubility pH being below about 4 or above about
12;

a first pH sensor configured to detect a pH level of the aqueous mixture;
a pH controller in communication with the first pH sensor configured to generate a first control signal to adjust the pH level
of the aqueous mixture to the solubility pH of below about 4 or above about 12 for treatment of the at least one undesirable
constituent in the wet oxidation reactor in response to the first pH sensor registering a pH level above about 4 or below
about 12; and

a second sensor in communication with the controller, the second sensor configured to detect a pH level of an oxidized aqueous
mixture formed in the wet oxidation unit, the pH controller configured to generate a second control signal to adjust the pH
level of the oxidized aqueous mixture to a second range at which the catalyst is substantially insoluble downstream of the
wet oxidation unit.

US Pat. No. 9,206,904

SEAL INCLUDING FLEXIBLE SEAL STRIPS

Siemens Energy, Inc., Or...

1. A seal assembly in a turbine engine having a housing and a rotatable shaft extending through the housing, a seal member
supported on the housing and provided in combination with the housing and the rotatable shaft to form the seal assembly with
the seal member positioned in sliding contact with the rotatable shaft and defining a seal preventing fluid flow in an axial
direction through an annular space formed between the housing and the rotatable shaft, the shaft rotating in a circumferential
direction, the seal assembly comprising:
a stator structure supported on the housing of the turbine engine;
a plurality of flexible seal strips, each said seal strip comprising a planar plate extending lengthwise radially through
the annular space and having a radially outer end supported to said stator structure and each said plate having a radially
inner end comprising a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral
surface of said rotatable shaft; and

at least one of said seal strips comprising a plurality of perforations extending through a thickness of said at least one
seal strip in the circumferential direction and arranged spaced from each other in the axial direction in a row located between
axially spaced leading and trailing edges of said at least one seal strip, said perforations defining an axially extending
hinge location radially outwardly from said radially inner end for effecting an increased flexing movement in the circumferential
direction of a portion of said at least one seal strip defined between said hinge location and said radially inner end, wherein
said increased flexing movement effected by said perforations is greater in the circumferential direction than in the axial
direction.

US Pat. No. 9,116,055

COMBUSTION TURBINE FLASHBACK SENSING SYSTEM EMPLOYING FIBER BRAGG GRATING SENSORS

Siemens Energy, Inc, Orl...

1. A combustion turbine flashback sensor cable, comprising:
an elongated optical fiber having a fiber Bragg grating (FBG) temperature sensor along the fiber;
an elongated tubular conduit having a hollow cavity circumscribing and retaining the optical fiber therein, the conduit having
a first thermal conductivity and a circumferential outer surface for exposure to combustion turbine combustion gasses; and

a sensor shield coupled to and forming a portion of the conduit circumferential outer surface, oriented in axial and circumferential
proximity to the FBG temperature sensor, having a second thermal conductivity greater than the first thermal conductivity.

US Pat. No. 9,810,099

TURBINE EXHAUST CYLINDER STRUT STRIP FOR SHOCK INDUCED OSCILLATION CONTROL

SIEMENS ENERGY, INC., Or...

11. A method for controlling fluid flow induced vibrations in a gas turbine diffuser, comprising:
disposing a protrusion on a turbine exhaust cylinder strut of the gas turbine exhaust diffuser;
coupling the protrusion to the turbine exhaust cylinder strut,
wherein the protrusion controls shock induced oscillations which minimizes pressure fluctuations in the gas turbine exhaust
diffuser such that an unsteadiness of fluid flow surrounding the turbine exhaust cylinder strut is reduced,

wherein the disposing includes positioning the protrusion on the suction side of the leading edge of a turbine exhaust cylinder
strut airfoil, and

wherein a distance from the leading edge of the turbine exhaust cylinder strut to a leading edge of the protrusion on the
suction side is in a range from 7.5% to 12% of the strut chord length.

US Pat. No. 9,808,885

METHOD FOR FORMING THREE-DIMENSIONAL ANCHORING STRUCTURES ON A SURFACE

SIEMENS ENERGY, INC., Or...

1. A method comprising:
applying a laser beam to a surface of a solid material to form a liquefied bed on the surface of the solid material;
applying a pulse of laser energy to at least a portion of the liquefied bed to cause a splash of liquefied material outside
the liquefied bed; and

forming on the surface of the solid material a three-dimensional anchoring structure upon solidification of the splash of
liquefied material;

wherein the applying of the pulse of laser energy to the portion of the liquefied bed is performed subsequent to the applying
of the laser beam to the surface of the solid material; and

wherein the applying of the laser beam to the surface of the solid material comprises a scanning by the laser beam over the
surface of the solid material.

US Pat. No. 9,810,434

TRANSITION DUCT SYSTEM WITH ARCUATE CERAMIC LINER FOR DELIVERING HOT-TEMPERATURE GASES IN A COMBUSTION TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. Apparatus for delivering hot-temperature gasses from a plurality of combustors in a combustion turbine engine to a first
row of turbine blades in the combustion turbine engine, the apparatus comprising:
an exit piece for each one of the plurality of combustors, wherein the exit piece comprises an arcuate connection segment
defining an arcuate flow path, wherein the arcuate connection segment forms an open perimeter, wherein the exit piece connects
to an adjacent exit piece at the arcuate connection segment of the adjacent exit piece, and the connection of the exit piece
and the adjacent exit piece defines a portion of an annular chamber, the annular chamber arranged to extend circumferentially
and oriented concentric to a longitudinal axis of the combustion turbine engine, for delivering the hot-temperature gasses
to the first row of blades, the exit piece comprising:

a metal outer shell and an arcuate ceramic liner inwardly disposed onto the metal outer shell along the arcuate connection
segment of the exit piece, wherein the arcuate ceramic liner forms an open liner perimeter in correspondence with the open
perimeter of the arcuate connection segment of the exit piece;

retainer structures disposed in the arcuate connecting segment of the exit piece to retain respective edges of the open liner
perimeter in the arcuate connecting segment of the exit piece, wherein the retainer structures are disposed at the respective
edges of the open perimeter of the arcuate connection segment of the exit piece, wherein the retainer structure comprises
a body comprising a first flange and a second flange interconnected by a web, the body circumferentially extending in the
arcuate connection segment of the exit piece, wherein the first flange and the second flange interconnected by the web define
a groove configured to receive a corresponding ceramic liner protrusion at the respective edge of the open liner perimeter
in the arcuate connection segment of the exit piece, the ceramic liner protrusion constituting a free end of the arcuate ceramic
liner;

wherein the exit piece further comprises a straight path segment defining a straight flow path for passing hot-temperature
gasses from a respective combustor of the plurality of combustors,

a straight ceramic liner inwardly disposed onto the metal outer shell along the straight path segment of the exit piece, wherein
the straight ceramic liner forms a closed liner perimeter and an open liner perimeter respectively in correspondence with
the closed perimeter and the open perimeter of the straight path segment of the exit piece,

wherein the straight path segment forms a closed perimeter starting at an inlet end of the straight path segment, wherein
the closed perimeter of the straight path segment of the exit piece changes to an open perimeter that is in fluid communication
with the portion of the annular chamber along a common plane between a convergence flow junction (CFJ) and an outlet end of
the straight path segment,

wherein the arcuate flow path and the straight flow path constitute individual flow paths that mutually converge at the convergence
flow junction.

US Pat. No. 9,612,016

FLAME MONITORING OF A GAS TURBINE COMBUSTOR USING MULTIPLE DYNAMIC PRESSURE SENSORS IN MULTIPLE COMBUSTORS

Siemens Energy, Inc., Or...

1. A flame monitoring method for a plurality of gas turbine engine combustors arranged for combusting fuel in a gas turbine
engine, comprising:
receiving a first dynamic sensor output signal from a first acoustic sensor positioned in a first gas turbine engine combustor,
the first dynamic sensor output signal containing components indicative of first acoustic oscillations generated by a first
flame within the first gas turbine engine combustor;

receiving a second dynamic sensor output signal from a second acoustic sensor positioned in a second gas turbine engine combustor,
the second dynamic sensor output signal containing components indicative of second acoustic oscillations generated by the
first flame within the first gas turbine engine combustor and propagated to the second acoustic sensor positioned in the second
gas turbine engine combustor;

performing a cross-correlation operation on the first and second dynamic sensor output signals to determine a cross-correlation
value between the first and second acoustic oscillations, the cross-correlation operation being constrained by a maximum time
delay between correlated components of the first and second acoustic oscillations; and

based on the cross-correlation value, determining whether the first flame is present within the first gas turbine engine combustor.

US Pat. No. 9,540,956

INDUSTRIAL GAS TURBINE EXHAUST SYSTEM WITH MODULAR STRUTS AND COLLARS

Siemens Energy, Inc., Or...

1. An industrial gas turbine exhaust system, comprising:
an inner case;
an outer case circumscribing the inner case in spaced relationship relative to a centerline defined by the exhaust system;
a turbine exhaust path defined between the outer and inner cases;
a plurality of struts interposed between the outer and inner cases that are tilted at an angle relative to a radius defined
by the exhaust system centerline; and

first and second strut collars respectively coupled to respective ends of each strut and its respective abutting outer or
inner case, each respective collar outer surface having a constant fillet radius external profile on an acute angle side thereof,
for smooth exhaust flow transition between its respective strut and abutting case surface, the fillet radius profile having
a range of 15%-40% of strut maximum thickness, each strut collar having a cross section thickness varying by no more than
10% at any circumferential location.

US Pat. No. 9,500,368

ALTERNATELY SWIRLING MAINS IN LEAN PREMIXED GAS TURBINE COMBUSTORS

SIEMENS ENERGY, INC., Or...

1. A can annular gas turbine combustor for producing hot gas by burning a fuel in compressed air comprising:
a combustor central axis, a plurality of main swirlers with respective swirler axes disposed about, equidistant from, and
parallel to the combustor central axis, each main swirler configured to deliver an air fuel mixture flowing therethrough about
the respective swirler axis, wherein airfoils of a first of two adjacent swirlers are concentric with and angled in a first
direction about a first swirler axis and airfoils of a second swirler axis such that during operation tangential components
of flow direction of meeting portions of adjacent air fuel mixtures travel in the same direction;

fuel injectors for distributing fuel within each main swirler air fuel mixture in a concentration other than a center rich
concentration; and

a central pilot swirler disposed on the central axis and delivering a pilot air fuel mixture flowing therethrough.

US Pat. No. 9,470,109

TURBINE BLADE INSERTION TOOL

Siemens Energy, Inc., Or...

1. A method for inserting a turbine blade root (18) of a turbine blade into a corresponding downwardly oriented turbine rotor slot (14) of a vertically suspended rotor (12), comprising:
providing a blade insertion tool (20) having:

a man-maneuverable base (22),

a vertical column (34, 36) projecting upwardly from the base having a distal end height adapted for passage under the vertically suspended rotor,

a blade lift fixture (46) defining a cavity (48) for slidable receipt and retention of the turbine blade root, therein, and

a three-axis degree of freedom joint (44, 50) for selectively coupling the distal end of the vertical column and the blade fixture;

slidably inserting and retaining the turbine blade root into the blade lift fixture;
raising the blade lift fixture with the turbine blade suspended there from;
coupling the blade lift fixture and the vertical column distal end with the joint, thereby vertically suspending and supporting
the blade with the blade insertion tool;

maneuvering the blade insertion tool under the vertically suspended rotor and coaxially aligning the turbine blade root and
rotor slot by maneuvering the suspended blade and the blade lift fixture;

sliding the turbine blade root at least partially into the rotor slot;
releasing the turbine blade root from the blade lift fixture; and
continue sliding the turbine blade root into the rotor slot until the blade is in a fully seated position on the rotor.

US Pat. No. 9,458,737

ADJUSTABLE BRACING APPARATUS AND ASSEMBLY METHOD FOR GAS TURBINE EXHAUST DIFFUSER

SIEMENS ENERGY, INC., Or...

1. A gas turbine exhaust assembly comprising:
a diffuser shell comprising a first section joined to a second section at a joint there between;
a plurality of pairs of bolt bosses along a length of the joint, wherein each pair of bolt bosses comprises a first bolt boss
on the first section and a second bolt boss on the second section, wherein the first and second bolt bosses of each respective
pair are opposed across the joint;

a casing around the diffuser shell;
a first plurality of length adjustable braces attached between the first section and the casing; and
a second plurality of length adjustable braces attached between the second section and the casing,
wherein the first and second pluralities of length adjustable braces form a series of pairs of turnbuckles, wherein each pair
of turnbuckles comprises a first radially oriented turnbuckle attached between the first section of the diffuser shell and
the casing by clevis fittings, and a second radially oriented turnbuckle welded or releasably attached between the second
section of the diffuser shell and the casing clevis fittings, wherein the first and second turnbuckles of each pair are opposed
across the joint,

wherein each of the clevis fittings comprises parallel first and second plates and a side plate that blocks a lower end of
a space between the first and second parallel plates, wherein when an eye of one of the turnbuckles is inserted between the
first and second parallel plates it is retained therein by gravity.

US Pat. No. 9,400,171

OPTICAL WEAR MONITORING

SIEMENS ENERGY, INC., Or...

1. A wear probe for monitoring wear of a part having a wearing surface, comprising:
an optical guide having a first end and a second end, wherein the first end is configured to be located flush with the wearing
surface such that as the wearing surface wears, the first end of the optical guide will wear as well so that the first end
remains flush with the wearing surface;

a fiber bundle having a first end and a second end, the first end of the fiber bundle located proximate to the second end
of the optical guide, the fiber bundle comprising:

a transmit fiber bundle comprising a first plurality of optical fibers; and
a receive fiber bundle comprising a second plurality of optical fibers;
a light source coupled with the second end of the transmit fiber bundle and configured to provide light to the second end
of the transmit fiber bundle for transmission of light from the first end of the transmit fiber bundle through the optical
guide to the first end of the optical guide;

a light detector coupled with the second end of the receive fiber bundle and configured to detect reflected light that is
reflected from the first end of the optical guide and is transmitted through the optical guide to be captured by the first
end of the receive fiber bundle; and

a processor configured to determine a length of the optical guide based on the detected reflected light.

US Pat. No. 9,366,600

LINEAR ARRAY TO IMAGE ROTATING TURBINE COMPONENTS

SIEMENS ENERGY, INC., Or...

1. A method of inspecting a component located on a rotor rotating about an axis internal to a turbine, comprising:
providing an elongated probe defining a probe length and having a one-dimensional pixel array formed by a plurality of pixels
extending single file along the probe length;

positioning the probe through an access port in a casing of the turbine;
rotating the rotor to move the component past the pixel array;
receiving at the pixel array energy emitted from an image area defined by a line extending along the component and lying in
a plane extending parallel to radial and axial directions in the turbine;

conveying an intensity-based signal from each pixel in the pixel array to a processor to convert the intensity-based signals
to an intensity-based line image; and

converting a succession of the intensity-based line images into a cohesive two-dimensional digital image of the component.

US Pat. No. 9,316,619

NON DESTRUCTIVE EVALUATION SCANNING PROBE WITH SELF-CONTAINED MULTI-AXIS POSITION ENCODER

Siemens Energy, Inc., Or...

1. A reflected penetrating waveform scanning probe for nondestructive evaluation of a non-living test sample, comprising:
a housing having an underside for abutment against and multi-dimensional translation across a surface of a non-living test
sample, and having directed outwardly toward the surface:

a test sensor system for transmitting a penetrating waveform into the test sample, receiving a reflected waveform from the
test sample at a multi-dimensional spatial location on the test sample surface and generating reflected waveform data corresponding
to that location; and

a probe position encoder system that correlates multi-dimensional probe underside translation and rotation motion across the
test sample surface with the multi-dimensional spatial location on the test sample surface and that generates corresponding
multi-dimensional spatial location data, said probe position encoder system having a pair of first and second orthogonal axes
position encoders respectively generating first and second orthogonal axes position readings, with the respective corresponding
orthogonal axes in mutual parallel alignment, said probe position encoder system compensating for probe rotation when the
respective first and second orthogonal axes position readings differ, while generating said multi-dimensional spatial location
data; and

a scan data acquisition system, coupled to the test sensor and encoder systems, for receiving and correlating corresponding
reflected waveform data at the location with its corresponding multi-dimensional spatial location data in a scan data set,
and for sending the scan data set to a nondestructive evaluation analyzer.

US Pat. No. 9,190,890

METHOD AND APPARATUS FOR REMOVAL AND REPLACEMENT OF A WOUND STATOR CORE

Siemens Energy, Inc., Or...

1. A method for removing a generator core, with windings, from a generator frame, the method comprising:
removing electrical and mechanical connections between the core and components external to the frame;
after the removing step, installing a first lift support assembly outboard of the core at an exciter end of the frame and
installing a second lift support assembly outboard of the core at a turbine end of the frame;

installing a first pilot shaft support assembly between an inner surface of a core bore and an outer surface of a pilot shaft
at the exciter end of the frame and installing a second pilot shaft support assembly between the inner surface of the core
bore and the outer surface of the pilot shaft at the turbine end of the frame, the first and second pilot shaft support assemblies
each supporting the pilot shaft by directly contacting the outer surface of the pilot shaft;

installing the pilot shaft through the first and second pilot shaft support assemblies and the core bore, the pilot shaft
supported by the first and second lift support assemblies at the respective exciter end and the turbine end;

decoupling the core and the frame; and
activating an axial force-producing device to exert an outwardly directed force on the core to slide the core on the pilot
shaft and out of the frame.

US Pat. No. 9,133,716

TURBINE ENDWALL WITH MICRO-CIRCUIT COOLING

Siemens Energy, Inc., Or...

1. A cooling module for an endwall in a vane assembly of a gas turbine engine, wherein the endwall includes a plurality of
micro-circuit cooling modules provided in compartments in the endwall, said micro-circuit cooling modules comprising an outer
perimeter rail, an upper plate, an upper channel proximate to the upper plate, a lower plate and a lower channel proximate
the lower plate all defining a mixing chamber therein, a first plurality of spaced apart strip elements extending along a
first direction in an upper channel of the mixing chamber, and a second plurality of spaced apart strip elements extending
along a second direction opposite to the first direction in the lower channel of the mixing chamber so that the first plurality
of strip elements and the second plurality of strip elements form a criss-cross configuration that creates airflow junctions
that cause the airflow to become turbulent and produce a high rate of heat transfer, wherein the density of the criss-cross
configuration is varied in the micro-circuit cooling modules based on endwall local heat load.

US Pat. No. 9,126,278

TEMPLATE FOR FORMING COOLING PASSAGES IN A TURBINE ENGINE COMPONENT

Siemens Energy, Inc., Or...

1. A system for forming a plurality of cooling passages in a component for use in a turbine engine comprising:
an electrode holder;
a plurality of electrodes extending from and structurally supported by the electrode holder; and
a template having a first surface defining an electrode entry surface, a second surface opposed from the first surface and
defining a component mating surface, and a plurality of electrode passages pre-formed in the template and extending from the
first surface to the second surface, the second surface of the template having a shape that corresponds to an outer surface
of the component such that the template is capable of being snugly positioned against the outer surface of the component,
wherein the template includes corresponding electrode passages for each of the cooling passages to be formed in the entire
surface of the component;

wherein, during an electro-discharge machining operation, the electrodes are simultaneously inserted through the pre-formed
electrode passages in the template and into the component while supplying an electric current to the electrodes to remove
material from the component so as to form the cooling passages therein.

US Pat. No. 9,103,011

SOLUTION HEAT TREATMENT AND OVERAGE HEAT TREATMENT FOR TITANIUM COMPONENTS

Siemens Energy, Inc., Or...

1. A method of fabricating a Ti-6AI-4V titanium alloy component comprising sequential steps of:
a) providing a forged Ti-6AI-4V titanium alloy component;
b) solution heat treating the component at a solution temperature relatively high within an alpha +beta two-phase field for
the material of the component and at least 54° F. below the beta transus temperature comprising a temperature within a range
of about 1675° F. to about 1775° F., and for a predetermined period of time;

c) cooling the component to a temperature below the temperature of the alpha +beta two-phase field;
d) overage heat treating the component comprising an overaging process at a predetermined overaging temperature comprising
a temperature greater than 1357° F. and less than 1500° F. for a predetermined time;

e) cooling the component from the predetermined temperature of step d) to room temperature; and
wherein the overaging temperature comprises a temperature lower than the solution temperature but higher than an aging heat
treatment temperature for effecting a maximum yield strength in the component, and wherein the resulting structure of the
component has a fracture toughness, KIC, greater than 50 ksi-in1/2and a yield strength greater than about 125 ksi.

US Pat. No. 9,810,081

COOLED CONDUIT FOR CONVEYING COMBUSTION GASES

SIEMENS ENERGY, INC., Or...

1. A conduit through which hot combustion gases pass in a gas turbine engine, the conduit comprising:
a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to
pass through the conduit, said wall structure comprising:

a forward end;
an aft end axially spaced from said forward end, said aft end defining a combustion gas outlet for the hot combustion gases
passing through the conduit;

a resonator structure including a plurality of resonator boxes for attenuating acoustic vibrations within the engine; and
a plurality of generally radially outwardly extending protuberances located in a circumferential band in said wall structure,
said protuberances each including at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter
said inner volume, wherein at least one of said protuberances is shaped so as to cause cooling fluid passing through it to
diverge in a circumferential direction as it enters into said inner volume and wherein said protuberances are aligned with
said resonator structure; and

wherein at least one of said protuberances defines a front portion, a pair of side portions, a radially outer portion including
a radially outermost wall portion, and a back portion, each of said front and back portions extending at an angle with respect
to said central axis, and said cooling fluid passage of said protuberance extends through said radially outermost wall portion
of said protuberance.

US Pat. No. 9,597,749

LASER WAVEGUIDE WITH COAXIAL FILLER WIRE FEED

SIEMENS ENERGY, INC., Or...

1. An apparatus comprising:
a laser waveguide comprising a wall configured to conduct a laser energy axially from a proximal end to a distal end of the
waveguide;

a hollow center of the waveguide that slidably guides a filler feed wire from the proximal end to the distal end of the waveguide;
and

a first laser emitter that delivers a first laser beam to the proximal end of the waveguide within an acceptance angle of
the waveguide;

wherein the laser energy emerges from the distal end of the waveguide with an energy distribution about the feed wire.

US Pat. No. 9,528,706

SWIRLING MIDFRAME FLOW FOR GAS TURBINE ENGINE HAVING ADVANCED TRANSITIONS

SIEMENS ENERGY, INC., Or...

1. A can-annular gas turbine engine combustion arrangement, comprising:
a rotor shaft rotating in a rotor shaft direction of rotation;
combustor cans each comprising a combustor outlet and a combustor inlet circumferentially offset from the respective combustor
outlet in a direction opposite the rotor shaft direction of rotation;

an axial compressor;
a plenum in fluid communication with all combustor inlets and providing fluid communication between the axial compressor and
the combustor inlets;

a means for inducing circumferential motion to compressed air in the plenum in the direction opposite the rotor shaft direction
of rotation, wherein the means for inducing circumferential motion comprises at least one row of rotating compressor airfoils
located upstream from a last row of the rotating compressor airfoils, the at least one row of rotating compressor airfoils
configured to impart a counter swirl velocity greater than a velocity of rotation of the rotating airfoils; and

a flow path for conveying the compressed air in the plenum to a respective combustor inlet of a respective combustor can.

US Pat. No. 9,452,484

METHOD FOR COMPONENT MACHINING BY ABLATION AND CONTROLLED RECAST LAYER REMOVAL BY FLUORIDE ION CLEANING

Siemens Energy, Inc., Or...

1. A method for machining a component, comprising:
establishing desired component shape and dimensions for a work piece machined surface to be formed by an electrical discharge
machining (EDM) or a laser machining ablation method, which creates a recast oxide layer on the machined surface;

establishing ablation machining speed and energy application rates for forming the machined surface to the desired component
shape and dimensions;

determining recast oxide layer thickness that will result from performing the ablation machining speed and energy application
rates, prior to said machining;

determining a fluoride ion cleaning (FIC) process that is intended to remove all of the previously determined oxide layer
thickness, prior to said cleaning;

ablation machining the work piece with an EDM or laser machining apparatus, at the established machining speed and energy
application rates, so that a resultant machined surface of the work piece conforms with the established component shape and
dimensions, forming a recast oxide layer of the previously determined thickness there upon;

performing the determined FIC process with FIC apparatus;
inspecting the work piece after completion of the FIC process, in order to confirm that the machined surface of the work piece
conforms with the established component shape and dimensions and that it has a clean surface, which has no recast layer.

US Pat. No. 9,455,613

ROTOR WINDING HAVING A BRAZE JOINT SPACED APART FROM STRESS CONCENTRATION

SIEMENS ENERGY, INC., Or...

1. A winding for a rotor having a rotor body, comprising:
a plurality of first axial sections located in a first slot of the rotor body;
a plurality of second axial sections located in a second slot of the rotor body;
a plurality of end arc sections, wherein each end arc section is oriented transverse to an associated axial section; and
first and second integrated leg sections that extend from each end arc section to form associated first and second corner
sections, respectively, wherein the first and second leg sections are affixed to associated first and second axial sections
located in the first and second slots, respectively, at first and second joints, respectively, wherein the first and second
joints are spaced apart from the first and second corner sections, respectively, by a distance such that the first and second
joints are not subjected to stress concentration which occurs at the first and second corner sections, respectively, thereby
connecting each end arc section between an associated first axial section in the first slot and an associated second axial
section in the second slot.

US Pat. No. 9,366,855

SYSTEM AND METHOD FOR ONLINE INSPECTION OF TURBINES INCLUDING TEMPERATURE AND VIBRATION COMPENSATING LENS MOUNT

SIEMENS ENERGY, INC., Or...

1. A camera lens system comprising:
an optical camera imaging lens, having a pair of first and second opposed axial faces, and a circumferential edge between
the faces; a lens mount having a bore confining the entire first lens therein, defining an inner surface circumscribing, retaining
and directly abutting at least a portion of the lens edge and allowing lens axial displacement therein, while restraining
lens radial displacement; a first mounting ring, entirely confined within the lens mount bore, said first ring having a pair
of first and second opposed axial faces, and a circumferential edge between the faces, said ring circumferential edge directly
abutting and slidably retained within the lens mount bore and inner surface, said ring first axial face in abutting contact
with the lens only along the first axial face of said lens, allowing lens axial displacement, a mounting rim defining the
second axial face and circumferential edge of said first mounting ring, and a plurality of flexible cantilever fingers respectively
having proximal ends coupled to the mounting rim, and distal ends projecting axially away from the rim, which define the first
axial face of said first mounting ring, said distal ends deflectable axially and radially inwardly with respect to the housing
inner surface, and are in biased abutting contact with the first lens only along the first axial face thereof; and a compression
spring biasing element entirely nested and confined within the lens mount bore inner surface, for exerting axially oriented
biasing force on the first lens first face through the first mounting ring first face during lens or ring axial displacement
caused by ambient temperature or pressure variations experienced by the camera lens system, with outward radial deflection
of said biasing element constrained by the lens mount inner surface; and wherein the lens mount as well as each respective
lens, mounting ring and biasing element are constructed of materials capable of continuous operation in a varying temperature
range up to greater than 1112 degrees Fahrenheit (600 degrees Celsius).

US Pat. No. 9,289,854

AUTOMATED SUPERALLOY LASER CLADDING WITH 3D IMAGING WELD PATH CONTROL

Siemens Energy, Inc., Or...

1. A system for cladding a turbine component having a substrate and a surface with a filler layer, comprising:
a work table apparatus for receipt of a turbine component substrate thereon, having a work table interface;
a laser profilometer apparatus for scanning a surface of the turbine component substrate and acquiring component dimensional
data, having:

a scanning laser generating a scanning laser beam for reflecting optical energy off the turbine component surface;
at least one movable scanning mirror intercepting the scanning laser beam, for orienting the scanning laser beam on the substrate
surface; and

a laser profilometer apparatus drive system interface coupled to the scanning laser and the at least one movable scanning
mirror, for causing relative movement there between;

a cladding filler material distribution apparatus for introducing filler material on the component substrate;
a laser welding apparatus for transferring optical energy to the turbine component substrate and filler material on the substrate
that fuses the filler material to the substrate as a built up filler layer that is applied as a welding pattern, having:

a welding laser generating a welding laser beam for transferring optical energy;
at least one movable welding mirror intercepting the welding laser beam, for orienting the laser beam on the substrate; and
a welding laser apparatus drive system interface coupled to the welding laser and the at least one movable welding mirror
for causing relative movement there between;

a drive system operatively coupled to the work table, the profilometer, the cladding filler material distribution apparatus,
the laser welding apparatus and their respective drive interfaces, for operating the apparatuses and providing controlled
relative motion there between; and

a control system operatively coupled to each of said apparatuses and their drive interfaces, for:
acquiring component dimensional data with the laser profilometer apparatus;
comparing the acquired component dimensional data with component specification dimensional data;
based on the comparing of component and specification dimensional data: determining respective filler introduction and/or
welding patterns for cladding component substrate surface portions to conform welded component dimensions to the specification
dimensional data; and

causing the filler apparatus and the laser welding apparatus execute their respective patterns in order to clad the component
substrate.

US Pat. No. 9,291,102

INTERFACE RING FOR GAS TURBINE FUEL NOZZLE ASSEMBLIES

SIEMENS ENERGY, INC., Or...

1. A gas turbine combustor assembly of a gas turbine comprising:
a cover plate having a cover plate inner diameter;
a combustor basket including a combustor liner supported on a downstream side of said cover plate, said combustor liner having
a combustor liner inner diameter;

a plurality of fuel nozzle assemblies arranged in an annular array inside said combustor liner, wherein each of said plurality
of fuel nozzle assemblies comprises a fuel injector and a swirler assembly, each swirler assembly including a main body, wherein
an upstream end of said main body of each swirler assembly comprises a bellmouth structure formed as a radially outwardly
curved portion at an entrance to said swirler assembly, said bellmouth structure being located upstream of said fuel injector
and an outer edge of said bellmouth structure at least partially defining a radially outer periphery with reference to a center
of said plurality of fuel nozzle assemblies in said annular array, wherein a radially outer portion of said outer edge of
each bellmouth structure is removed to define a flattened area; and

an interface ring provided between said combustor liner inner diameter and said plurality of fuel nozzle assemblies and located
axially at said upstream end of said main body of each swirler assembly, wherein said interface ring includes a surface that
is substantially contiguous with at least a portion of said flattened area of each of said bellmouth structure, said interface
ring comprising a radially inner edge defining an interface ring inner diameter and a radially outer edge defining an interface
ring outer diameter;

wherein said radially outer edge of said interface ring is located adjacent to and contacts said combustor liner inner diameter;
and

wherein each of a plurality of portions of said radially inner edge of said interface ring spans between said at least a portion
of said flattened areas of two adjacent ones of said bellmouth structures, an air passage being defined between each of said
plurality of portions of said radially inner edge and said flattened areas of said two adjacent ones of said bellmouth structures,
wherein each air passage is located circumferentially between two fuel nozzle assemblies of said plurality of fuel nozzle
assemblies.

US Pat. No. 9,182,285

METHODS REGARDING OPTICAL PROBE HAVING AN INNER TUBE WITH SEPARABLE TUBE SECTIONS TO HOUSE OPTICAL ELEMENTS

SIEMENS ENERGY, INC., Or...

1. In an optical probe having an inner tube arranged to house at least one optical element, a method comprising:
constructing the inner tube to have at least two cooperating inner tube sections separable from one another along respective
joint lines co-axially extending in a direction along a longitudinal axis over an entire longitudinal length of the inner
tube;

while the at least two cooperating inner tube sections are detached from one another, disposing into either of the inner tube
sections the at least one optical element; and

attaching to one another the at least two cooperating inner tube sections by way of at least one affixing element.

US Pat. No. 9,808,889

GAS TURBINE INCLUDING SEALING BAND AND ANTI-ROTATION DEVICE

SIEMENS ENERGY, INC., Or...

1. A turbine comprising:
a plurality of stages, each stage comprising a rotatable disk and blades carried thereby, at least one pair of adjacent rotatable
disks defining an annular gap therebetween and having respective opposing sealing band receiving slots aligned with the gap;

a sealing band located in said opposing sealing band receiving slots to seal said annular gap;
disk engagement structure defined in said pair of adjacent rotatable disks; and
a clip member coupled to said sealing band and in engagement with said pair of adjacent rotatable disks through said disk
engagement structure, said clip member having an aperture extending only part way through said clip member and used during
assembly of said clip member to said sealing band, said clip member restricting movement of said sealing band.

US Pat. No. 9,455,611

PROCESS FOR ASSEMBLING A STATOR CORE ASSEMBLY

SIEMENS ENERGY, INC., Or...

1. A process for assembling a stator core assembly comprising:
providing first and second stator core modules;
wherein said first stator core module comprises a first main body comprising a plurality of first core rings, first and second
through-holes in said first main body, first and second counter-bores aligned with said first and second through-holes, respectively,
and first and second fastener assemblies extending through said first and second through-holes, respectively; and

said second stator core module comprises a second main body comprising a plurality of second core rings, a third through-hole
in said second main body, a third counter-bore, and a third fastener assembly extending through said third through-hole, wherein
said third fastener defines a protruding fastener assembly on said second stator core module;

positioning said first stator core module adjacent said second stator core module such that said protruding fastener assembly
on said second stator core module nests in said first counter-bore provided in said first stator core module; and

coupling said first and second stator core modules to one another.

US Pat. No. 9,358,629

TUNGSTEN SUBMERGED ARC WELDING USING POWDERED FLUX

SIEMENS ENERGY, INC., Or...

1. A method comprising;
depositing a layer of powder comprising a powdered flux material onto a surface of a superalloy substrate;
forming an arc within the layer of powder between a non-consumable electrode and the substrate;
melting at least a portion of the flux material and a superalloy feed material with the arc to form a layer of cladding material
covered by a layer of slag on the substrate; and

allowing the cladding material to cool and to solidify under the layer of slag.

US Pat. No. 9,359,955

APPARATUS AND METHOD INCORPORATING A TRANSITION AFT SUPPORT FOR A GAS TURBINE ENGINE

Siemens Energy, Inc., Or...

1. An apparatus for supporting an aft portion of a transition duct in a gas turbine engine, comprising:
an annular shaped stator component disposed in a turbine section of the gas turbine engine,
a transition aft frame that engages with the stator component, the transition aft frame comprising a radially outer panel,
a radially inner panel, and circumferentially spaced first and second side panels connecting the radially inner and radially
outer panels,

wherein a forward face of the stator component comprises a first connection point and a second connection point spaced apart
in a circumferential direction, each of the connection points comprising a respective slot,

wherein the transition aft frame comprises first and second attachment structures that respectively engage with the first
and second connection points on the forward face of the stator component when the transition duct is aligned axially with
the stator component, the first and second attachment structures being spaced apart, the spacing being effective to transfer
moment load from the first and second attachment structures to the first and second side panels respectively,

wherein each of the attachment structures comprises a link that is rotatable about a tangential axis, and
wherein an aft end of the link comprises a tangential pin that is engageable with a corresponding one of said slots on the
forward face of the stator component, the link being rotatable about the center of the pin upon engagement of the pin in the
slot.

US Pat. No. 9,347,328

COMPRESSED AIR PLENUM FOR A GAS TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. A compressed air supply system for routing compressed air from a compressor to at least one combustor of a gas turbine
engine, comprising:
a plurality of plenums, each plenum having an upstream end in fluid communication with an inner chamber of the compressor
in which air is compressed and having a downstream end in fluid communication with the at least one combustor;

wherein the plurality of plenums comprises a plurality of plenums meshed together such that mouths at the upstream end of
the plenums form a continuous ring radially outward from compressor blades;

wherein each of the plenums extend downstream from the mouth generally tangential to a flow path of an outermost point on
a compressor blade and extends axially, wherein the plenum curves radially outward such that the plenum extends generally
radially outward; and

a flow conditioner at a downstream end of the at least one plenum that is formed from a cylindrical exhaust opening surrounded
by the at least one plenum that is larger than a diameter of the cylindrical exhaust opening.

US Pat. No. 9,316,399

LEAN-RICH AXIAL STAGE COMBUSTION IN A CAN-ANNULAR GAS TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. A method for axial stage combustion in a gas turbine engine comprising:
mixing air and fuel to form a lean air-fuel mixture of air and fuel in a first stage of combustion of a can-annular combustor
of the gas turbine engine, wherein the lean air-fuel mixture of air and fuel has an equivalence ratio of less than one;

igniting the lean air-fuel mixture at the first stage of combustion to create hot combustion gas having a first temperature
and free radicals;

disposing an air-fuel mixing arrangement in a second stage of combustion of the can-annular combustor, the second stage of
combustion located downstream from the first stage of combustion, the air-fuel mixing arrangement coupled to receive fuel
delivered in the second stage of combustion by a plurality of fuel nozzles and further coupled to receive a flow of air in
the second stage of combustion;

mixing air and fuel received by the air-fuel mixing arrangement to form a rich air-fuel mixture of air and fuel in the second
stage of combustion, wherein the rich air-fuel mixture of air and fuel has an equivalence ratio of greater than one;

wherein the mixing of air and fuel received by the air-fuel mixing arrangement comprises adjustably varying a volumetric flow
rate of fuel delivered in the second stage of combustion by the fuel nozzles by way of respective valves in each fuel nozzle
to adjustably vary the equivalence ratio of the rich air-fuel mixture,

injecting the rich air-fuel mixture into the second stage of combustion; and
igniting the rich air-fuel mixture in the hot combustion gas at the second stage of combustion, such that the first temperature
and the free radicals of the hot combustion gas promote combustion of the rich air-fuel mixture within a predetermined hydrocarbon
emissions limit, and the first temperature of the hot combustion gas increases to a second temperature.

US Pat. No. 9,309,774

ASSEMBLY FOR DIRECTING COMBUSTION GAS

SIEMENS ENERGY, INC., Or...

1. An arrangement for delivering gases from a plurality of combustors of a can-annular gas turbine combustion engine to a
first row of turbine blades, the arrangement comprising a gas path cylinder, a cone, and an integrated exit piece (IEP) for
each combustor, wherein each IEP comprises a straight path portion for receiving a gas flow from a respective combustor via
the cylinder and cone, and the IEP further includes a connection segment, wherein each IEP connects to an adjacent IEP at
the connection segment of the adjacent IEP, and the connected IEPs define an annular chamber that extends circumferentially
and is oriented concentric to a gas turbine engine longitudinal axis, for delivering the gas flow to the first row of blades;
wherein gases flow from respective combustors, through respective straight path portions, and into the annular chamber;
wherein each straight path portion comprises four side walls forming a closed polygonal cross section at an inlet end of the
straight path portion, adjacent pairs of side walls being connected by radiused joints, defined by four radiused joints extending
from an upstream location toward an exit end of the IEP, at least two of the joints having a constant radius from the upstream
location to the exit end and at least one of the joints having a radius that is greater than the radii of the at least two
joints;

wherein the four side walls of the straight path portion are defined by a radially outer side wall opposite to a radially
inner side wall, and the radially outer and inner side walls are coupled together with opposed forward and aft side walls,
and the forward side wall defines a continuous side wall from an upstream end of the straight path portion to the exit end
of the IEP;

wherein the inner side wall is bounded by forward and aft longitudinal edges extending in the direction of a flow axis for
the straight path portion, the connection segment includes a connection segment forward wall extending circumferentially from
an upstream location to a downstream edge, and including a flared fillet, having longitudinal edges that diverge in a downstream
flow direction, extending from the aft longitudinal edge of the inner side wall to the downstream edge of the connection segment
forward wall.

US Pat. No. 9,186,757

METHOD OF PROVIDING A TURBINE BLADE TIP REPAIR

Siemens Energy, Inc., Or...

1. A method of repairing a turbine blade having a radially extending outer wall defining an internal cavity width and a blade
tip, the method comprising:
removing at least a portion of the blade tip to form a repair surface;
providing a tip cap having a radially outer side with an outer width less than said internal cavity width and a radially inner
side with an inner width substantially equal to or greater than said internal cavity width;

positioning said tip cap at said repair surface such that said radially outer side does not overlap said outer wall, wherein
a notch is formed between a periphery of said tip cap and said repair surface;

performing a first welding operation welding said tip cap to said repair surface, said first welding operation including forming
a weld bead using a first welding material filling in said notch around the periphery of said tip cap; and

performing a second welding operation including build-up welding to form a cap peripheral portion using a second welding material,
different from said first welding material, formed over said first welding material and extending on said repair surface between
said tip cap and an outer surface of said outer wall;

wherein said first welding material forming said weld bead filling in said notch has a higher ductility than a ductility of
said second welding material forming said cap peripheral portion, and wherein, following said second welding operation, said
first welding material remains in said notch separating said second welding material from contact with said tip cap and said
repair surface at said notch.

US Pat. No. 9,151,171

STEPPED INLET RING FOR A TRANSITION DOWNSTREAM FROM COMBUSTOR BASKET IN A COMBUSTION TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. A hot gas path system for a gas turbine, comprising:
at least one outer housing forming a combustor basket;
at least one transition section that extends from a position downstream of a terminal end of the combustor basket;
a stepped inlet ring coupled to the at least one transition section and extending upstream from the at least one transition
section, wherein an upstream end of the stepped inlet ring is positioned radially outward from the combustor basket such that
at least a portion of the stepped inlet ring axially overlaps a portion of the combustor basket, wherein the stepped inlet
ring is formed from a radially extending, generally cylindrical collar coupled to an axially extending cylindrical wall;

at least one spring clip positioned between the combustor basket and the stepped inlet ring such that the at least one spring
clip seals at least a portion of a circumferential gap between the combustor basket and the stepped inlet ring; and

at least one heat shield positioned downstream from the combustor basket and proximate to an intersection between the collar
and the axially extending cylindrical wall, wherein the at least one heat shield contacts the collar and contacts the axially
extending cylindrical wall of the stepped inlet ring.

US Pat. No. 9,140,193

GAS TURBINE IGNITER WITH STRUCTURE TO REDUCE RADIAL MOVEMENT OF IGNITER ROD

SIEMENS ENERGY, INC., Or...

1. A gas turbine igniter comprising:
a guide tube;
an igniter rod disposed in the guide tube and extending from a hot-end region to a cold-end region;
a piston connected to the igniter rod, the piston located proximate the hot-end region;
a cap connected to the guide tube, wherein the cap defines an access passageway to the igniter rod; and
wherein the piston abuts a portion of the igniter rod to reduce a range of radial movement of the igniter rod in the access
passageway.

US Pat. No. 9,120,690

VORTEX AIR INLET SYSTEM, COMPRESSOR SYSTEM AND RELATED METHOD

Siemens Energy, Inc., Or...

1. An aeration system for a waste water treatment plant having multiple water treatment aeration basins, comprising:
a controller; and
a plurality of modular compressor systems each allocated to a different basin in an aeration system, each compressor system
including (i) an air inlet system for receiving ambient air and discharging cleaned air and (ii) at least one compressor unit
positioned to receive the cleaned air and to output compressed air, the air inlet system designed to be placed on top of the
at least one compressor unit,

each compressor unit including a compressor and a processor based control unit responsive to commands received from the controller,
wherein:

the controller is coupled to receive data from (i) a plurality of dissolved oxygen sensors each positioned to receive data
from a different one of the basins, (ii) multiple flow meters indicative of air flow into each basin, and the controller is
operatively coupled to adjust air flow into each of the basins;

each control unit is coupled to respond to the controller to adjust the air flow into a basin and is also operatively linked
to other components in the unit to adjust power input to the compressor, blow-off pressure during compressor start-up and
valve controls to effect cooling of components in the unit; and

each compressor system comprises a series of modular, vertically stackable units with anchoring of one unit to another unit
to provide a stable structure in which the air inlet system is positioned above the compressor.

US Pat. No. 9,109,457

AXIAL LOCKING SEALS FOR AFT REMOVABLE TURBINE BLADE

SIEMENS ENERGY, INC., Or...

1. A turbine assembly having an array of turbine blades that can be disassembled downstream without removing a turbine casing,
the assembly comprising:
a rotor disk having an axis of rotation and extending axially from a forward, intake side to an aft, exhaust side;
said rotor disk having axially extending disk grooves spaced about its circumference;
an array of turbine blades, each turbine blade having an airfoil terminating in a blade platform and blade root;
a turbine casing arranged to radially surround the array of turbine blades;
each blade root being axially mounted in one of said disk grooves;
said rotor disk providing adjacent its aft, exhaust side a radially outward facing circumferential groove adjacent an inner
tappet;

each of the turbine blades providing a circumferential groove along its blade platform facing the circumferential groove of
the rotor disk;

each of said blade roots providing an outer tappet;
a plurality of seal plates, each plate have an outer edge mounted in at least one of the turbine blade circumferential grooves,
each plate having an inner edge mounted in rotor disk circumferential groove;

said plurality of seal plates collectively at the aft, exhaust side of the rotor disk locking the turbine blades from axial
movement by engagement with the inner and outer tappets, wherein the blades are axially secured from the aft, exhaust side
and can be axially removed from the aft, exhaust side without lifting the turbine casing, wherein each blade root and platform
are unrestrained from rearward axial movement by any structure on the forward, intake side of the rotor disk; and

a spacer disk positioned on the forward, intake side of the rotor disk, said spacer disk including a radially extending sealing
arm effective to engage the blade root of at least one of the turbine blades without axially restraining rearward axial movement
of the blade root and platform, wherein said array of blades is removable in the aft, exhaust direction by access just to
the aft, exhaust side of the rotor disk without removing or disassembling the turbine casing.

US Pat. No. 9,101,877

SELECTIVE CATALYTIC REDUCTION SYSTEM AND PROCESS FOR CONTROL OF NOX EMISSIONS IN A SULFUR-CONTAINING GAS STREAM

Siemens Energy, Inc., Or...

1. A process for selective catalytic reduction of nitrogen oxides (NOx) with effective suppression of ammonia salt formation
in a gas stream comprising ammonia, the NOx, SO2 and water, the process comprising:
reducing the NOx via the ammonia by passing the gas stream over a catalytic bed comprising a reducing only catalyst portion
that comprises a first amount of tungsten; and

oxidizing remaining ammonia while simultaneously further reducing NOx by passing the gas stream over a reducing-plus-oxidizing
catalyst portion downstream from the reducing only catalyst portion in the catalytic bed, the reducing-plus-oxidizing catalyst
portion comprising a second amount of tungsten greater than the first amount of tungsten.

US Pat. No. 9,090,487

WATER TREATMENT APPARATUS INCORPORATING WET AIR REGENERATION AND POWDERED ACTIVATED CARBON TREATMENT

SIEMENS ENERGY, INC., Or...

1. A water treatment apparatus comprising:
a powdered activated carbon treatment (PACT) system;
a wet air regeneration (WAR) system in fluid communication with the PACT system and configured to regenerate spent carbon
from the PACT system; and

a solubles concentration reduction apparatus in fluid communication between the PACT system and the WAR system and configured
to reduce a concentration of a soluble material associated with the spent carbon upstream of the WAR system, wherein the solubles
concentration reduction apparatus comprises:

a dewatering device coupled to receive sludge containing the soluble material from the PACT system and to produce dewatered
sludge;

a re-slurrying device coupled to receive the dewatered sludge from the dewatering device and to produce re-slurried sludge,
wherein the re-slurrying device comprises a re-slurry tank configured to receive the dewatered sludge from the dewatering
device, and is further configured to receive the water essentially free of the soluble material, wherein the re-slurrying
device further comprises a sensor coupled to supply a signal indicative of a content weight in the re-slurry tank, and a controller
coupled to receive the signal from the sensor and configured to calculate a rate of content weight change in the re-slurry
tank, the controller further configured to generate in response to the calculated rate of content weight change a control
signal for selectively actuating a valve which controls an amount of water added to the dewatered sludge.

US Pat. No. 9,057,271

SPLICE INSERT REPAIR FOR SUPERALLOY TURBINE BLADES

Siemens Energy, Inc., Or...

1. A repaired turbine blade comprising, a turbine blade body that defines a hollow portion and an excavated recess having
a curved profile that facilitates repair splice insertion from inside the hollow portion toward an exterior surface of the
blade body, the recess profile defined by a radius of curvature axis that is generally parallel to an adjoining hollow portion
defined interior surface or exterior surface of the blade body and laterally offset therefrom; and
a mating, mechanically interlocking repair splice inserted and captured within the recess, with the repair splice affixed
to the blade body for retention thereof, having a repair splice outer profile conforming to the radiused curve recess profile.

US Pat. No. 10,046,416

METHOD OF WELD CLADDING OVER OPENINGS

SIEMENS ENERGY, INC., Or...

1. A method, comprising:providing a component including at least two walls separated by a first opening;
spanning the first opening with a support structure configured to divide the first opening into a plurality of second openings wherein the plurality of second openings are smaller than the first;
supporting the support structure with a supporting powder;
melting alloy filler to form a melt pool traversing across the plurality of second openings while in contact with and supported by the support structure;
allowing the melt pool to cool and to solidify to form a cladding layer that covers the first opening and the at least two walls and is metallurgically bonded with the support structure; and
removing the supporting powder after the cooling and solidifying.

US Pat. No. 9,527,173

ALIGNMENT TOOL FOR USE IN ALIGNING OPENINGS IN STRUCTURAL MEMBERS

Siemens Energy, Inc., Or...

14. An alignment tool for aligning a first structural opening in a first member with a second structural opening in a second
member, the first and second members to be coupled by insertion of a fastener through the first and second structural openings,
the tool comprising:
a back plate;
a first lug defining a first lug opening therein and adjustably coupled to the back plate for linear displacement relative
to the back plate;

a second lug defining a second lug opening therein, the second lug fixedly mated to the back plate;
a first pin received within the first lug opening and extending in a first direction from the first lug opening for receiving
within a third structural opening in the first member, the third structural opening proximate the first structural opening;

the first lug adjustably coupled to the back plate such that a distance between the back plate and the first pin is adjustable;
a second pin received within the second lug opening and extending in a second direction from the second lug opening for receiving
within a fourth structural opening in the second member, the fourth structural opening proximate the second structural opening,
the first direction opposite the second direction; and

wherein reducing the distance between the back plate and the first pin displaces the third structural opening toward the back
plate to align the first and second structural openings thereby permitting insertion of a fastener through the first and second
structural openings to couple the first and second members.

US Pat. No. 9,518,895

OPTICAL PROBE WITH IMPROVED AFFIXING STRUCTURE FOR SUPPORTING A LIGHT-REDIRECTING ELEMENT

SIEMENS ENERGY, INC., Or...

1. An optical probe comprising:
an inner tube; and
a light-redirecting element disposed at a distal end of the inner tube, wherein the light-redirecting element is supported
at said distal end by an affixing structure not attached to an optically-working surface of the light-redirecting element,
wherein the inner tube comprises at least two corresponding inner tube sections separable from one another along respective
joint lines co-axially extending in a direction along a longitudinal axis over an entire longitudinal length of the inner
tube, wherein the light-redirecting element comprises a prism, wherein the affixing structure comprises respective protrusions
from the inner tube sections, each protrusion having a support surface attached to a corresponding lateral surface of the
prism, wherein the affixing structure further comprises respective layers of adhesive between the support surfaces and the
lateral surfaces of the prism.

US Pat. No. 9,513,117

SITU BLADE MOUNTED TIP GAP MEASUREMENT FOR TURBINES

Siemens Energy, Inc., Or...

1. A method for measuring gas turbine blade tip and turbine ring segment radial clearance gap, comprising:
providing a gas turbine including: a turbine casing having an inner circumferential ring segment that fully circumscribes
a rotatable rotor oriented within the casing, the rotor having a row of turbine blades radially aligned with the ring segment,
each blade having an airfoil that defines an airfoil outer surface and a radially outwardly projecting tip in opposed, spaced
relationship with the circumscribing ring segment, each respective blade tip defining a radial clearance gap between itself
and the circumscribing ring segment at a plurality of rotational angular positions of the blade and rotor;

coupling on an airfoil surface of a first one of said blades at least one non-contact displacement sensor that generates a
displacement data set of distance between the displacement sensor and the ring segment;

coupling on the airfoil surface of the same first one of said blades a rotor rotational position sensor that generates a rotational
position data set indicative of rotational angular orientation of said first blade relative to the circumscribing ring segment;

rotating the rotor so that the blade tip of said first blade sweeps at least a portion of the circumscribing ring segment,
while generating the displacement data set with the displacement sensor and a rotational position data set with the rotor
rotational position sensor at plural angular positions along the blade tip sweep;

acquiring the displacement and rotational position data sets with a data acquisition system that is coupled to the displacement
and rotational position sensors; and

correlating blade tip and circumscribing ring segment radial clearance gap relative to angular rotational position of said
first blade, with the displacement and rotational data sets, at plural angular positions along the blade tip sweep, in a data
analyzer system that is coupled to the data acquisition system.

US Pat. No. 9,494,532

SYSTEM AND METHOD FOR SIDE-BY-SIDE INSPECTION OF A DEVICE

Siemens Energy, Inc., Or...

1. A method for inspection, comprising:
one or more users arranging a plurality of movable cameras in a known position relative to a gas turbine machine, the plurality
of movable cameras being mounted on a controllable actuator having a first arm and a second arm, the controllable actuator
being controlled by a computing device, the first arm being enabled to move linearly inside the gas turbine machine, the second
arm attached to the first arm being enabled to be rotated relative to the first arm in two perpendicular planes, the second
arm supporting one of the plurality of movable cameras enabled to be placed in a plurality of positions inside the gas turbine
machine;

the computing device retrieving a Computer-Aided-Design (CAD) model of the gas turbine machine to be inspected;
the computing device pointing the one of the plurality of movable cameras at the inside of the gas turbine machine;
the computing device controlling the controllable actuator to position the one of the plurality of movable cameras at a first
position with a user interface on the computing device;

the computing device rendering an inside image from a virtual view of the one of the plurality of movable cameras in the first
position into the CAD model of the gas turbine machine with the computing device;

the computing device displaying an image of the gas turbine machine generated by the one of the plurality of movable cameras
in the first position, which is an image of the gas turbine machine in a used state, on a display;

the computing device causing the image from the virtual view of the one of the plurality of movable cameras in the first position
into the CAD model of the gas turbine machine, which is an inside image of the gas turbine machine in an unused state, to
be displayed on the display; and

the computer device performing inspection using the CAD model of the gas turbine machine and the image both displayed simultaneously
on the display.

US Pat. No. 9,410,853

GUIDED WAVE THERMOGRAPHY METHODS AND SYSTEMS FOR INSPECTING A STRUCTURE

SIEMENS ENERGY, INC., Or...

1. A method to inspect a structure, the method comprising:
transmitting guided sonic or ultrasonic waves controlled to directionally selectively focus energy to any desired region throughout
the structure, wherein the energy is sufficient to cause a thermal response indicative of a structural flaw which may be located
at the at least one region of the structure;

identifying guided wave modes that meet boundary conditions of the structure;
selectively forming at least one of the identified guided wave modes that meets the boundary conditions of the structure;
and

sensing the thermal response indicative of the flaw.

US Pat. No. 9,359,902

TURBINE AIRFOIL WITH AMBIENT COOLING SYSTEM

Siemens Energy, Inc., Or...

1. A turbine airfoil, comprising:
a generally elongated hollow airfoil formed from an outer wall, and having a leading edge, a trailing edge, a pressure side,
a suction side, a root at a first end of the airfoil and a tip at a second end opposite to the first end, and an ambient air
cooling system positioned within interior aspects of the generally elongated hollow airfoil;

at least one cooling channel of the ambient air cooling system in the generally elongated hollow airfoil extending radially
outward from an inlet at a proximal end of the root, the at least one cooling channel being configured to receive ambient
air at atmospheric pressure;

wherein the ambient air cooling system has a tip static pressure to ambient pressure ratio of at least 0.5; and
wherein the ambient air cooling system comprises a plurality of cooling channels extending from the root to the tip and terminating
at an outlet at the tip of the airfoil, wherein the outlet at an outer surface of the tip is aligned with inner surfaces forming
the cooling channels in the airfoil, wherein at least one of the cooling channels includes a combination of low and high friction
factor augmenting cooling components to promote beneficial flow splits.

US Pat. No. 9,181,819

COMPONENT WALL HAVING DIFFUSION SECTIONS FOR COOLING IN A TURBINE ENGINE

Siemens Energy, Inc., Or...

1. A component wall in a turbine engine comprising:
a substrate having a first surface and a second surface opposed from said first surface;
a plurality of diffusion sections located in said second surface, each said diffusion section defined by a bottom surface
between said first and second surfaces, an open top portion located at said second surface, and wall structure extending outwardly
continuously from said bottom surface to said second surface, said wall structure surrounding the respective diffusion section
and comprising at least a first sidewall, a second sidewall opposed from said first sidewall, a third sidewall extending between
said first and second sidewalls, and a fourth sidewall opposed from said third sidewall and extending between said first and
second sidewalls, said third and fourth sidewalls diverging from each other;

wherein:
said bottom surface of each said diffusion section is substantially parallel to said second surface, said bottom surface extending
from said first sidewall to said second sidewall and from said third sidewall to said fourth sidewall;

said first sidewall of each said diffusion section comprises a protuberance extending toward said second sidewall of the respective
diffusion section, each said protuberance formed by a pair of diverging wall portions, said diverging wall portions diverging
from each other at a greater angle than an angle of divergence of said third and fourth side walls and intersecting said third
and fourth sidewalls at respective downstream junctions;

each said diffusion section comprises a single cooling passage, said cooling passage of each said diffusion section extending
through said substrate from said first surface to said bottom surface of the respective diffusion section, wherein an outlet
of each said cooling passage is arranged within the respective diffusion section such that cooling air exiting each said cooling
passage through said outlet is directed toward said protuberance of the respective first sidewall; and

said outlet of said cooling passage includes opposed first and second side edges, said first side edge being generally parallel
to said third sidewall of said respective diffusion section and said second side edge being generally parallel to said fourth
sidewall of said respective diffusion section.

US Pat. No. 9,175,373

INERTIA FRICTION WELD OF SUPERALLOY WITH ENHANCED POST WELD HEAT TREATMENT

Siemens Energy, Inc., Or...

1. A method of inertia friction welding a superalloy substrate, the method comprising:
rotating and forcing a deposit material against the superalloy substrate;
plastically deforming at least one of the deposit material and the superalloy substrate to form a weld joint joining the deposit
material to the superalloy substrate, thereby forming an assembly; and

heat-treating the assembly, wherein the heat-treating comprises a post-weld intermediate stress-relief (ISR) treatment at
an ISR treatment temperature below a solutionizing temperature of the superalloy substrate, followed by a solutionizing treatment,
followed by a precipitation hardening heat treatment.

US Pat. No. 9,175,604

GAS TURBINE ENGINE WITH HIGH AND INTERMEDIATE TEMPERATURE COMPRESSED AIR ZONES

Siemens Energy, Inc., Or...

1. A gas turbine engine, comprising:
a combustor within a combustion air plenum, wherein the combustor intakes combustion air from the combustion air plenum;
a compressor comprising a final stage that supplies the combustion air to the combustion air plenum; and
a transition piece within a cooling air plenum, wherein the cooling, air plenum receives cooling air bled from a bleed port
of an intermediate stage of the compressor;

wherein the transition piece channels a combustion gas from the combustor.

US Pat. No. 9,174,314

ISOTHERMAL STRUCTURAL REPAIR OF SUPERALLOY COMPONENTS INCLUDING TURBINE BLADES

Siemens Energy, Inc., Or...

1. A method for repairing a cracked superalloy component, comprising:
providing a superalloy component with a substrate region having a crack therein;
heating the substrate region to a desired isothermal hold temperature in a range of between above 800° C. (1472° F.) and below
said substrate's incipient melting point;

melting superalloy filler in a heater;
isothermally filling the crack at least partially with molten superalloy filler poured from the heater; and
solidifying the cast superalloy filler to form a diffusion bonded, crack-free patch, without any significant localized melting
of the substrate material that might otherwise induce solidification crack formation.

US Pat. No. 9,116,071

SYSTEM AND METHOD FOR VISUAL INSPECTION AND 3D WHITE LIGHT SCANNING OF OFF-LINE INDUSTRIAL GAS TURBINES AND OTHER POWER GENERATION MACHINERY

Siemens Energy, Inc., Or...

1. A system for internal three-dimensional scanning inspection of a turbine, comprising:
a base for affixation to a turbine inspection port,
an inspection scope having an extendable elongated body defining a central axis, with a proximal end rotatively coupled to
the base and a distal end for insertion within a turbine inspection port;

a camera housing defining a central axis, for insertion within a turbine inspection port, having:
a proximal end coupled to the inspection scope distal end,
a distal end, and
a structured light 3D scanner having a stripe projector for projecting a band of photons on an inspection surface of interest
within a turbine interior, and a matrix camera having an optical path for capturing images of reflected photons that were
projected on the inspection surface.

US Pat. No. 9,097,117

TURBINE TRANSITION COMPONENT FORMED FROM AN AIR-COOLED MULTI-LAYER OUTER PANEL FOR USE IN A GAS TURBINE ENGINE

SIEMENS ENERGY, INC, Orl...

1. A transition duct for routing gas flow in a combustion turbine subsystem that includes a first stage blade array having
a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction, said
circumferential direction having a tangential direction component, an axis of the rotor assembly defining a longitudinal direction,
and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of
the first stage blade array, said transition duct, comprising:
a transition duct body having an internal passage extending between an inlet and an outlet;
wherein the duct body is formed at least in part from a multi-panel outer wall; and
wherein the multi-panel outer wall is formed from an inner panel having an inner surface that defines at least a portion of
a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling
chamber is formed between the inner and intermediate panels;

at least one rib extending from the inner panel radially outward into contact the intermediate panel;
an outer panel positioned radially outward from the intermediate panel such that at least one cooling chamber is formed between
the intermediate and outer panels;

an attachment system comprising at least one seal body integrally formed with the inner panel and having at least one portion
extending radially outward with at least one pocket configured to receive a side edge of the intermediate panel in a sliding
arrangement such that the intermediate panel is able to move in-plane relative to the attachment system and to receive a side
edge of the outer panel in a sliding arrangement such that the outer panel is able to move in-plane relative to the attachment
system.

US Pat. No. 9,085,478

DISTRIBUTED AERATION SYSTEM AND CONTROL ARCHITECTURE

Siemens Energy, Inc., Or...

1. A compressor system providing for removal of particulate matter from cleaned air which enters the compressor, comprising:
a compressor for generating compressed air with the cleaned air;
a compressor housing, having an upper surface, enclosing the compressor;
a vortex air cleaner positioned over the compressor housing, coupled to an intake of the compressor to receive ambient air
and provide the cleaned air as an output to the intake during compressor operation, the vortex air cleaner comprising a plurality
of cyclone separators positioned to drop particles removed from the ambient air over the upper surface of the compressor housing;

a supply line coupled to receive compressed air output from the compressor; and
an air sweep coupled to receive a portion of the compressed air and positioned to emit the compressed air over the upper surface
of the housing to remove particles dropped from the vortex air cleaner.

US Pat. No. 9,085,042

STUD WELDING REPAIR OF SUPERALLOY COMPONENTS

Siemens Energy, Inc., Or...

1. A joined superalloy component comprising:
a superalloy substrate defining a recess having a recess profile;
a mating superalloy stud having a stud projection captured within the substrate recess, with a projection profile conforming
with the entire substrate recess profile along a contact surface; and

the substrate and stud affixed to each other along the entire contact surface by a process of stud welding by:
inserting the stud and substrate in a stud welding apparatus;
orienting the stud projection and substrate recess in an opposed spaced relationship with a gap there between;
passing current between the stud projection and recess and forming an arc there between with the stud welding apparatus;
melting the opposed stud projection and substrate recess opposed surfaces; and
pressing the melted stud projection and substrate recess opposed surfaces into contact with each other along the entire contact
surface, thereby forming a weld there between and extruding excess weld outside of the recess.

US Pat. No. 9,654,741

SYSTEM AND METHOD FOR OPTICAL FIBER BASED IMAGE ACQUISITION SUITABLE FOR USE IN TURBINE ENGINES

SIEMENS ENERGY, INC., Or...

1. A system for image acquisition suitable for use in a turbine engine, said system comprising:
a coded-aperture mask, said coded-aperture mask having a plurality of apertures configured for projecting light received from
a field of view in an object plane onto an image plane, wherein said coded-aperture mask is characterized by a first transfer
function,

an image conduit, said image conduit comprising a set of imaging fibers arranged to form an image acquisition end and an image
processing end, said image acquisition end being arranged to substantially coincide with said image plane such that each imaging
fiber acquires light projected onto a corresponding region within said image plane, and transfers said light to said image
processing end, wherein said image conduit is characterized by a second transfer function,

a sensor array, said sensor array comprising a set of light sensing elements arranged to receive light from individual imaging
fibers at said image processing end, and generate corresponding sampled image signals in a sensing basis, and

a signal processing device, said signal processing device configured for transforming said sampled image signals from said
sensing basis to a representation basis and generating a set of estimated image signals therefrom based on said first and
second transfer functions, wherein said representation basis provides a sparser representation of said sampled image signals
relative to said sensing basis, and further wherein the number of estimated image signals is greater than the number of sampled
image signals to increase image resolution for a given number of imaging fibers in said image conduit and reduce a number
of imaging fibers to provide an image conduit having a reduced form-factor to enable access to regions of interest within
the turbine engine,

wherein the image conduit is enabled to access regions that are less than 8 mm in diameter,
wherein the intensity pattern of light on the image plane is related to the intensity pattern of the light in the object plane
through the first transfer function, and

wherein the light intensity on the image processing end is related to the light intensity on the acquisition end through the
second transfer function.

US Pat. No. 9,502,938

WRAPPED STATOR COIL FOR USE IN A GENERATOR

SIEMENS ENERGY, INC., Or...

1. A wrapped stator coil for use in a generator comprising:
an electrical conductor coil;
an insulating layer structure disposed about the electrical conductor coil;
an interwoven layer structure disposed about the insulating layer structure and comprising insulating material and a first
conductive material; and

a conductive layer structure disposed about the interwoven layer structure and comprising a second conductive material,
wherein the second conductive material has a lower resistance than the first conductive material.

US Pat. No. 9,453,767

ACTIVE TEMPERATURE MONITORING IN GAS TURBINE COMBUSTORS

SIEMENS ENERGY, INC., Or...

1. A method for actively monitoring temperature in a combustor of a gas turbine engine, comprising:
placing in a gas turbine combustor at least one acoustic transmitter and at least one thermoacoustic sensor that is oriented
in a distinct line-of-sound path from the transmitter, the sensor capable of generating sensor output signals indicative of
thermoacoustic oscillations, including combustion thermoacoustic oscillations and wherein the combustor includes at least
one sensor that is in pressure communication with combustor working gasses;

coupling the at least one transmitter and the at least one sensor to a controller that is capable of causing the at least
one transmitter to transmit acoustic signals within the combustor and capable of correlating sensor output signals with combustion
conditions, including at least combustion temperature;

transmitting acoustic signals from the at least one transmitter;
receiving the acoustic signals from the at least one acoustic transmitter and generating dynamic sensor output signals with
the at least one thermoacoustic sensor that includes contributions of the received acoustic signals;

determining, using a processor, the time-of-flight for the acoustic signals traveling along each of the line of sound paths;
processing, via a processor, the time-of-flight for the acoustic signals traveling along the line of sound paths to determine
respective combustor path temperature along each respective line-of-sound path; and

determining bulk temperature within the combustor by:
identifying one or more acoustic frequencies in a respective sensor output signal;
determining, for each of the one or more acoustic frequencies, a first bulk temperature value, T, that is directly proportional
to each one of the one or more acoustic frequencies and a calculated constant value corresponding to each of the one or more
acoustic frequencies;

comparing the bulk first temperature value determined for each of the one or more frequencies to the path temperature and,
for each of the one or more frequencies, changing the calculated constant values to recalculated constant values based on
the comparison; and

determining subsequent first temperature values at the first location based on further identified acoustic frequencies.

US Pat. No. 9,400,217

DUAL INFRARED BAND APPARATUS AND METHOD FOR THERMALLY MAPPING A COMPONENT IN A HIGH TEMPERATURE COMBUSTION ENVIRONMENT

SIEMENS ENERGY, INC., Or...

1. An apparatus comprising:
an optical imaging probe housed in a viewing tube, the optical imaging probe having a field of view arranged to fully encompass
a surface of a component to be thermally mapped in a high temperature combustion environment of a turbine engine, the imaging
optical probe effective to concurrently capture infrared (IR) emissions that fully encompass the surface of a component, the
IR emissions comprising a first band in an IR spectrum, wherein the first band in the IR spectrum comprises a near IR wavelength
or comprises a mid IR wavelength, wherein the component of the turbine engine comprises a thermal barrier coating (TBC) subject
to emittance variation in the combustion environment of the turbine engine;

an optical fiber housed in the viewing tube, a field of view of the optical fiber arranged to encompass a spot location on
the surface of the component disposed within the field of view of the optical probe, the optical fiber effective to capture
IR emissions comprising a second band in the IR spectrum, wherein the second band in the IR spectrum comprises a long IR wavelength
effective to measure with a higher degree of accuracy emittance values from the TBC than the wavelengths in the first band,
the IR emissions in the second band in the IR spectrum indicative of an emittance value of the TBC at the spot location on
the surface of the component effective to reduce temperature errors due to the emittance variation of the TBC; and

a processor configured to calibrate a spot position error in connection with the spot location on the surface of the component
by way of an IR laser beam transmitted through the optical fiber,

wherein the laser beam impinges on the surface of the component on a laser-radiated location expected to correspond with the
spot location, and

wherein the optical probe is configured to capture IR emissions comprising a response to the impinging laser beam, the response
indicative of the spot position error in connection with the spot location.

US Pat. No. 9,394,618

SYSTEM AND METHOD FOR CLEANING STATOR COOLING COILS

SIEMENS ENERGY, INC., Or...

1. A method for removing cuprous oxide deposits from a copper-containing cooling system, comprising:
introducing a complexing agent into a fluid coolant that flows through the cooling system and a generator stator cooled by
the cooling system, wherein the complexing agent is selected to form a complex with cuprous ions and wherein the flow of fluid
coolant through the cooling system and generator stator is maintained when the complexing agent is introduced into the fluid
coolant; and

removing a mixture of the complexing agent and the fluid coolant from the cooling system after at least a portion of the complexing
agent has formed a complex with at least a portion of the copper contained in the cuprous oxide deposits wherein the flow
of fluid coolant through the cooling system and generator stator is maintained when the mixture of the complexing agent and
the fluid coolant is removed from the cooling system and wherein the introduction of the complexing agent and removal of complexing
agent and fluid coolant are performed simultaneously.

US Pat. No. 9,388,988

GAS TURBINE COMBUSTION CAP ASSEMBLY

Siemens Energy, Inc., Or...

1. A combustor cap assembly of a gas turbine engine, comprising:
a primary feed plate attached across an upstream end of a support ring;
a fuel/air premix tube within the support ring, the pre-mix tube comprising an upstream flange that aligns and seats the fuel/air
pre-mix tube against the primary feed plate,

the fuel/air premix tube further comprising an intermediate flange which is fixed on an outer surface of the fuel/air premix
tube at an intermediate position along the fuel/air premix tube; and

an intermediate structural frame at an intermediate location along the pre-mix tube having an opening through which the fuel/air
premix tube passes, wherein the opening is sized such that the intermediate flange cannot pass through;

wherein the intermediate flange contacts the intermediate structural frame and the intermediate structural frame restricts
longitudinal movement of the fuel/air premix tube relative to the support ring.

US Pat. No. 9,316,493

METHOD AND APPARATUS FOR DETERMINING GAS TURBINE DAMPENING CONE INNER DIAMETER

Siemens Energy, Inc., Or...

1. A method for determining internal diameter of a ring-shaped, dampening cone for gas turbine engine, comprising:
providing a measurement fixture, which includes:
a base defining a self-standing, elevated, planar reference surface;
a single locating pin projecting upwardly from an elevated upper end of the defined planar reference surface, the locating
pin defining a single contact surface;

a displacement indicator, coupled to base, having a displaceable point with a displacement range of motion below the contact
surface of the locating pin, along a displacement axis that is parallel to the planar reference surface and aligned with the
contact surface;

resting an axial end surface of a ring-shaped dampening cone of a gas turbine engine upon the elevated, planar reference surface
of the base, supported in an elevated position by hanging an inner radial surface of the dampening cone in abutting engagement
with only the single locating pin's single contact surface, while an opposite side inner radial surface thereof abuts against
and circumscribes the displacement indicator's displaceable point; and

determining the dampening cone inner diameter by swinging, in pendulum-like fashion, the dampening cone relative to the locating
pin single contact surface, the dampening cone inner diameter constituting distance from the locating pin's single contact
surface to the displacement indicator maximum-extension displacement reading.

US Pat. No. 9,272,363

HYBRID LASER PLUS SUBMERGED ARC OR ELECTROSLAG CLADDING OF SUPERALLOYS

Siemens Energy, Inc., Or...

17. A method comprising:
applying heat via an energy beam during a submerged arc or electroslag process to simultaneously melt a powder material and
a wire or strip feed material to form a composition of a desired superalloy material in a melt pool under a floating slag
layer;

allowing the melt pool to cool and solidify under the slag layer; and
removing the slag layer to reveal a clad layer of the desired superalloy material.

US Pat. No. 9,188,016

MULTI-ORIFICE PLATE FOR COOLING FLOW CONTROL IN VANE COOLING PASSAGE

Siemens Energy, Inc., Or...

1. A turbine vane for improving efficiency of a gas turbine engine, said turbine vane comprising:
a vane body, said body comprising a machined casting including an airfoil section with one or more internal cooling air passages
including a trailing edge cooling air passage which takes a three-pass serpentine route through the turbine vane, where the
machined casting has a design which is not to be changed;

a thermal barrier coating (TBC) covering an exterior surface of the airfoil section, where the TBC has a thickness which reduces
a maximum operating temperature in the vane body below a temperature of a surrounding combustion gas; and

an impingement plate fitted to an outer end of the vane body, where the impingement plate meters a flow of cooling air onto
the outer end of the vane body, and where the impingement plate includes a flow metering plate located over an inlet to the
trailing edge cooling air passage, where the flow metering plate controls a cooling air flow rate at an amount sufficient
to maintain the maximum operating temperature in the turbine vane below a prescribed limit value in conjunction with the thickness
of the TBC.

US Pat. No. 9,151,921

APPARATUS FOR MAKING UNIFORM OPTICAL FIBER BUNDLES IN POWER GENERATORS

Siemens Energy, Inc., Or...

1. A fiber hoop comprising a single piece plastic member having a circular shape including a central circular opening defining
a continuous outer perimeter piece, said outer perimeter piece including a center mandrel configured to accept wound strands
of one or more fiber optic cables and two opposing side guards raised away from the mandrel from the central opening, said
side guards being configured to hold the one or more fiber optic cables on the mandrel and to hold a fiber coupler such that
the fiber coupler is raised above the wound strands of the fiber optic cable and the fiber coupler is secured to an inside
surface of one of the side guards.

US Pat. No. 9,127,550

TURBINE SUPERALLOY COMPONENT DEFECT REPAIR WITH LOW-TEMPERATURE CURING RESIN

Siemens Energy, Inc., Or...

1. A turbine superalloy component, comprising:
a superalloy material turbine vane or blade temperature, resistant up to approximately 1100 degrees Celsius temperature, with
a substrate surface having a void;

particle-filled, hardened and cured resin layer filling the void, the resin curable under 200 degrees Celsius temperature,
and temperature resistant up to approximately 1100 degrees Celsius temperature;

a bond coat layer on the substrate surface and resin layer; and
a thermal barrier coating on the bond coat and resin layer;
sequential layers of the respective resin, bond coat, and thermal barrier coating remaining intact when exposed to turbine
operating temperature up to approximately 1100 degrees Celsius.

US Pat. No. 9,127,554

GAS TURBINE ENGINE WITH RADIAL DIFFUSER AND SHORTENED MID SECTION

Siemens Energy, Inc., Or...

1. An industrial gas turbine engine, comprising:
a can annular combustion assembly, comprising a plurality of discrete flow ducts configured to receive combustion gas from
respective combustors and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for
delivery directly onto a first row of turbine blades without guide vanes, and an annular chamber configured to merge the plurality
of discrete flow ducts into a single, annular flow duct defining an annular flow path immediately upstream of the first row
of turbine blades; and

a compressor diffuser positioned at a downstream end of an axial compressor and configured to receive an axial flow of compressed
air from the axial compressor, the compressor diffuser comprising a diffuser radially outer wall, a diffuser radially inner
wall, and a diffuser outlet there between, the diffuser radially inner wall comprising a redirecting surface configured to
receive the axial flow of compressed air and redirect the axial flow of compressed air radially outward along a path that
bypasses the annular chamber;

wherein the axial flow of compressed air exiting the downstream end of the axial compressor comprises all compressed air exiting
the downstream end of the axial compressor;

wherein the redirecting surface extends in a radial direction, relative to a longitudinal axis of the industrial gas turbine
engine, beyond a radially inner surface of the annular chamber, and into a plenum surrounding the can annular combustion assembly.

US Pat. No. 9,091,180

AIRFOIL ASSEMBLY INCLUDING VORTEX REDUCING AT AN AIRFOIL LEADING EDGE

SIEMENS ENERGY, INC., Or...

1. An airfoil assembly for an axial flow gas turbine engine, the gas turbine engine including an axially directed flow path
defining a passage for a working fluid and a source of pressurized fluid, the airfoil assembly including:
an endwall having an upstream edge and a downstream edge axially spaced from the upstream edge;
an airfoil extending from the endwall into the flow path, the airfoil having a leading edge and a trailing edge, and a pressure
side and a suction side extending between the leading and trailing edges;

the endwall is defined on a platform structure having a front surface adjacent to the upstream edge, the front surface extending
parallel to a radial direction, along a direction of a thickness of the platform structure;

at least one fluid injection passage extending through the platform structure in a direction from the upstream edge toward
the downstream edge, and each fluid injection passage having an outlet opening defined at the endwall and an inlet opening
in fluid communication with a pressurized fluid source;

each fluid injection passage extending through the platform structure at a shallow angle relative to a plane of the endwall
wherein the extension of each fluid injection passage through the platform structure defines a passage axis passing through
the front surface and the endwall,

wherein the respective outlet opening of each fluid injection passage is located axially between the upstream edge of the
endwall and the leading edge of the airfoil, and

wherein the respective passage axis along which each fluid injection passage extends through the platform structure is oriented
at an angle relative to the plane of the endwall that is in a range from about 10 to 20 degrees.

US Pat. No. 9,909,918

ULTRASONIC SCANNING DEVICE HAVING A FLUID PAD

Siemens Energy, Inc., Or...

1. An ultrasonic scanning device for scanning an object, comprising:
a moveable fluid distribution block that is moveable relative to a surface of the object, wherein the block includes a block
opening and an internal passageway for receiving a fluid, wherein the internal passageway is in fluid communication with the
block opening;

an ultrasonic transducer attached to the block; and
a fluid pad having a fluid pad opening that is in fluid communication with the block opening, wherein the fluid pad and block
openings form a channel that extends between the ultrasonic transducer and the object and wherein fluid received by the internal
passageway moves to the channel and forms a fluid column between the ultrasonic transducer and the object that facilitates
transmission of ultrasonic energy generated by the ultrasonic transducer wherein the fluid pad includes fibers that extend
from the fluid pad and contact the surface wherein the fibers substantially conform to more than one contour of the surface
as the block moves relative to the surface.

US Pat. No. 9,588,007

METHOD AND APPARATUS FOR TURBINE ENGINE ROTOR AUTOMATIC SELF BALANCING

SIEMENS ENERGY, INC., Or...

1. An online real time turbine engine rotor balancing system, comprising:
a rotor having a rotation axis;
a balancing ring perpendicular to the rotational axis and establishing a balance plane, said balancing ring including a radially
oriented bore establishing a displacement path in the balance plane;

a selectively displaceable balancing weight coupled to the rotor and adapted for being displaced along the displacement path;
a motor coupled to the balancing weight and the rotor, for selectively displacing the balancing weight along the displacement
path;

a turbine engine rotor vibration monitoring system for monitoring rotor vibration in real-time; and
a control system coupled to rotor vibration monitoring system and the motor, for determining in real time a desired balance
weight displacement position to counteract the monitored rotor vibration and selectively causing the motor to displace the
balancing weight to the desired displacement position along the displacement path.

US Pat. No. 9,540,941

INTERSTAGE SEAL ASSEMBLY FOR GAS TURBINE ENGINE

Siemens Energy, Inc., Or...

1. A seal assembly for a turbine engine including adjacent upstream and downstream rotating rotor disks supporting respective
rows of blades, a row of stationary vanes located between said rows of blades, and an axially extending rotor arm supported
on each said rotor disk and located radially inward from said blades, the seal assembly comprising:
an annular labyrinth seal holder supported on a radially inner end of said vanes and having a radially inner surface and a
downstream axially facing surface;

a plurality of radially extending labyrinth seal elements supported on said radially inner surface of said labyrinth seal
holder in axially spaced relation to each other;

a brush seal assembly supported to said labyrinth seal holder downstream from said labyrinth seal elements, said brush seal
assembly including a brush seal holder and a brush seal comprising seal bristles having fixed ends supported to said brush
seal holder and free ends located adjacent to an axially rearward one of said rotor arms, said brush seal holder being attached
to said axially facing surface of said labyrinth seal holder; and

a seal plate defining a detachable labyrinth seal element extending radially inward from said labyrinth seal holder to said
rearward rotor arm at a location upstream of said brush seal, said seal plate being sandwiched between said labyrinth seal
holder and said brush seal holder;

wherein said brush seal assembly is mounted to said labyrinth seal holder by a plurality of circumferentially spaced bolts
extending through said brush seal holder and said labyrinth seal holder, and said bolts extend through holes in said seal
plate to circumferentially position said seal plate.

US Pat. No. 9,520,224

USE OF ALUMINA PAPER FOR STRAIN RELIEF AND ELECTRICAL INSULATION IN HIGH-TEMPERATURE COIL WINDINGS

SIEMENS ENERGY, INC., Or...

1. A coil comprising:
a conductor formed in the shape of winding layers, the conductor comprising an insulating coating surrounding a conductive
core; and

a coil core having a shape defining corners;
winding layers disposed around the coil core; and
paper disposed between the winding layer adjacent the coil core and the coil core at the corners, and between winding layers,
the paper comprising aluminum dioxide fibers or strands disposed between one or more of the winding layers to provide both
strain relief against mechanical forces exerted on the coil and electrical insulation between winding layers at temperatures
up to 550 degrees C.; and

adhesive material, wherein the paper and the adhesive material are disposed between adjacent winding layers,
wherein the adhesive material is disposed between an outer surface of the coil core and the paper.

US Pat. No. 9,506,839

RETAINING RING ONLINE INSPECTION APPARATUS AND METHOD

SIEMENS ENERGY, INC., Or...

1. A method for inspecting a retaining ring of a dynamoelectric machine, the method comprising:
placing an optical device in a stationary component of the dynamoelectric machine and directing the optical device toward
a radial view of the retaining ring;

wherein the retaining ring includes a cylindrical body positioned on a rotatable rotor of the dynamoelectric machine, the
cylindrical body including an annular edge having a radial height;

using the optical device during rotation of the rotor, obtaining and transmitting an image of a circumferential portion of
the annular edge of the retaining ring;

identifying a location of one or more stress cracks forming and visible at the circumferential portion of the annular edge;
determining a structural condition for at least one location on the retaining ring using a metric including one or more of
a) a measured stress crack length, b) a measured stress crack width, and c) a counted number of stress cracks on the annular
edge; and

comparing the structural condition for the at least one location on the retaining ring using a value of the metric with a
predetermined acceptable value of the metric to identify whether the value of the metric exceeding the predetermined acceptable
value of the metric,

wherein the predetermined acceptable value of the metric comprises one or more of a predetermined acceptable value of a stress
crack length, a predetermined acceptable value of a stress crack width, and predetermined acceptable value of a number of
stress cracks on the annular edge.

US Pat. No. 9,404,421

STRUCTURAL SUPPORT BRACKET FOR GAS FLOW PATH

SIEMENS ENERGY, INC., Or...

1. A structural support system for a can annular gas turbine engine having an arrangement for delivering gases from a plurality
of combustors to a first row of turbine blades, the arrangement comprising an integrated exit piece (IEP) for each combustor,
the IEPs being joined together to form an annular chamber that extends circumferentially and is oriented concentric to a gas
turbine engine longitudinal axis for delivering a gas flow to the first row of blades, the structural support system for the
arrangement comprising:
an inner support structure located axially forward from the arrangement;
a bracket structure having a forward end connected to the inner support structure and having a rearward end connected to a
radially inner side of a respective IEP of the plurality of IEPs, the bracket structure including:

an axial bracket member having a first end located at the rearward end of the bracket structure and a second end axially aligned
with the inner support structure, and the second end being located in circumferentially spaced relation to the inner support
structure; and

a transverse bracket member having a first end connected to the second end of the axial bracket member and having a second
end circumferentially spaced from the first end of the transverse bracket member and forming the forward end of the bracket
structure attached to the inner support structure.

US Pat. No. 9,188,021

STEAM TURBINE BLADE VIBRATION MONITOR BACKPRESSURE LIMITING SYSTEM AND METHOD

Siemens Energy, Inc., Or...

1. A method for monitoring and controlling power plant steam turbine blade vibration within a designated safe operation range,
limiting backpressure on the blades by altering the turbine output load, comprising:
sampling in real time with sensors coupled to steam power plant equipment a plurality of types of operation states that impact
steam turbine blade vibration, including among others steam turbine blade vibration amplitude and backpressure on the blades;

storing in a first automated data storage device at least one sampled data reading for each respective type of operation state;
determining in real time a likelihood of whether one or a combination of the respective at least one sampled operation state
data readings is indicative of steam turbine blade vibration safe operation by:

referencing in a second automated data storage device previously stored information associating operation states with steam
turbine blade vibration; comparing at least one stored operation state sample reading from each respective type of sampled
operation state with respective stored association information relevant thereto and making respective turbine blade vibration
safe operation first confidence level determinations;

comparing a combination of the at least one stored sample reading from each respective type of sampled operation state with
respective stored association information relevant thereto, if such combination information is available, and making respective
turbine blade vibration safe operation second confidence level determinations; and

combining all prior sequentially determined confidence levels information to derive a turbine blade vibration safe operation
overall confidence level;

causing the steam turbine to lower turbine load incrementally when any of the sequentially determined first through overall
confidence levels is below a desired margin of safe operation; and

causing the steam turbine to increase turbine load incrementally when the overall confidence level is indicative of turbine
blade vibration safe operation.

US Pat. No. 9,177,371

NON-DESTRUCTIVE EXAMINATION DATA VISUALIZATION AND ANALYSIS

Siemens Energy, Inc., Or...

1. A method for assessing and interpreting non-destructive examination data collected with regard to a component under evaluation,
comprising:
acquiring non-destructive examination data that is collected with reference to an industrial component under evaluation, wherein
the non-destructive examination data includes a plurality of measurands that are derived from at least one non-destructive
examination method that measures conditions of the component under evaluation;

acquiring position information that associates the collected measurands to corresponding positions associated with the component
under evaluation;

automatically transforming by a computer processor the acquired measurands and corresponding position information, which comprise
data that is not in a format representative of an image of the component under evaluation into a visualization defined by
a volumetric representation that is rendered on at least one display device as at least one view representative of the component
under evaluation; and

utilizing a graphical user interface that interacts with the processor to navigate the volumetric representation to investigate
the integrity of the industrial component including non-surface conditions thereof by:

adjusting at least one view of the visualization to display a representation of at least a portion of the component under
evaluation;

distinguishing indications of discontinuities within at least one view that represents flaws associated with the structure
of the industrial component under evaluation that are not of interest from flaws of interest to an inspector;

utilizing the graphical user interface to measure at least one of a size, location and orientation of each detected indication
of a discontinuity that is of interest to the inspector; and

wherein automatically transforming by a computer processor the acquired the acquired measurands and corresponding position
information further comprises:

displaying the volumetric representation of the component in a first view comprising a three-dimensional representation of
the image; and

concurrent with displaying the first view, displaying the volumetric representation of the component in a plurality of concurrent
additional views that each comprises a two-dimensional representation of the component and each concurrent additional view
having respective coordinates and magnification parameters that are independently selectable; and

utilizing a graphical user interface that interacts with the processor to navigate the volumetric representation further comprises
controlling the displayed representation in each displayed view such that navigation in any displayed view automatically navigates
to the same location in each displayed view;

wherein:
automatically transforming by a computer processor the acquired measurands and corresponding position information further
comprises:

rendering, in response to inspector selection, the visualization based upon a selected one of:
non-destructive examination data from a single non-destructive examination sensor associated with a single non-destructive
examination method;

non-destructive examination data from multiple non-destructive examination sensors associated with a single non-destructive
examination method, where the multiple sensor data is fused into the same volumetric representation for display in at least
one view; and

non-destructive examination data from at least one non-destructive examination sensor associated with at least two non-destructive
examination methods, where each sensor data is fused into a single volumetric representation for display in at least one view;
and

rendering, in response to inspector selection, the visualization based upon a selected one of:
non-destructive examination data from at least one non-destructive examination sensor associated with at least two non-destructive
examination methods comprises fusing Eddy Current inspection data to Ultrasonic inspection data; and

utilizing a graphical user interface that interacts with the processor to navigate the volumetric representation further comprises:
displaying a user selectable control, having a first choice and a second choice, each choice related to a respective one of
two different methods of fusing the Eddy Current inspection data and the Ultrasonic inspection data;

receiving user input selecting one of the first choice or the second choice; and
fusing the Eddy Current inspection data and the Ultrasonic inspection data according to the method associated with the selected
choice.

US Pat. No. 9,129,742

GAS TURBINE ENGINE COMPRISING AN ULTRA HIGH TEMPERATURE CIRCUIT COUPLING OPEN CORE TRANSFORMER

Siemens Energy, Inc., Or...

1. A circuit coupling in a high temperature device with stable inductance throughout an operating temperature range between
an ambient temperature and a maximum operating temperature ranging up to at least 500 degrees Celsius, the circuit coupling
comprising:
an air gap core transformer positioned for operation as a telemetry transformer in an operating environment characterized
by the maximum operating temperature, and having a primary induction coil assembly and a secondary induction coil assembly
in proximity to one another with an air gap distance there between, the transformer characterized by a total inductance less
than 100 micro-H during operation at temperatures less than 150° C. and throughout the operating temperature range, wherein
the total inductance varies less than ten percent over a range extending from less than 150° C. to at least 500° C.,

the primary induction coil assembly comprising a solid primary core material, characterized by a Curie temperature which exceeds
that of nanostructured steel, and a primary coil wound about the primary core material, which coil maintains electrical conductivity
of itself and maintains electrical isolation from nearby conductors at temperatures in excess of the maximum operating temperature
range, the primary coil comprising a metal having a melting point temperature which exceeds that of copper, and

the secondary induction coil assembly comprising a solid secondary core material characterized by a Curie temperature which
exceeds that of nanostructured steel, and a secondary coil wound about the secondary core material, which coil maintains electrical
conductivity and maintains electrical isolation from nearby conductors at temperatures in excess of the maximum operating
temperature range, the secondary coil comprising a metal having a melting point temperature which exceeds that of copper,
wherein the primary core material is not connected to the secondary core material.

US Pat. No. 9,121,288

TURBINE BLADE WITH TUNED DAMPING STRUCTURE

Siemens Energy, Inc., Or...

1. A turbine blade comprising:
a root;
an airfoil comprising an external wall extending radially from said root and having a radially outermost portion, said external
wall comprising first and second side walls joined together at leading and trailing edges to define an inner cavity of said
airfoil; and

a damping structure positioned within said airfoil inner cavity and coupled to said airfoil so as to define a tuned mass damper,
said damping structure including a width dimension extending between said first and second side walls and a length dimension
greater than said width dimension extending in a direction between said leading and trailing edges, and said damping structure
comprising:

a damping element having a first end and a second end, said first end being coupled to said airfoil and said second end being
free to move within said airfoil inner cavity;

a tip mass member formed of a high density material different from a material defining said damping element and attached to
said second end of said damping element; and

said tip mass member movable with said second end of said damping element in a direction toward and away from said side walls.

US Pat. No. 9,102,015

METHOD AND APPARATUS FOR FABRICATION AND REPAIR OF THERMAL BARRIERS

Siemens Energy, Inc, Orl...

1. A method for fabricating a thermal barrier of a gas turbine component, comprising:
determining at least one material property of an existing thermal barrier coating on the component, the material property
selected from the group consisting of modulus of elasticity, thermal conductivity, and coefficient of thermal expansion, wherein
a value of said at least one material property is determined as a function of operating temperature and operating duration
of the existing thermal barrier coating; and

disposing a first layer of a metal brazing material in a die case;
disposing a second layer of a ceramic material on the metal brazing material; and
co-sintering the first and second layers in the die case with spark plasma sintering to form a co-sintered ceramic/metal tile
comprising a metal brazing layer, a ceramic thermal barrier layer, and a co-sintered interface there between; and

controlling the co-sintering to make the ceramic/metal tile to match the value of said at least one material property within
10% over an expected range of operating temperatures and time.

US Pat. No. 10,072,514

METHOD AND APPARATUS FOR ATTACHING A TRANSITION DUCT TO A TURBINE SECTION IN A GAS TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. An apparatus for attaching a transition duct to a turbine section of a gas turbine engine, comprising:an annular shaped vane carrier structure comprising a radial recess,
a transition aft frame that engages with the vane carrier structure, the transition aft frame comprising an outwardly extending clamp that is at least partially inserted into the recess,
a spacer inserted into the recess whereby the clamp and the spacer are arranged axially adjacent to each other within the recess, wherein a first pair of mating surfaces is formed by a first end face of the spacer and an end face of the clamp and a second pair of mating surfaces is formed by a second end face of the spacer and a wall of the recess, wherein the first pair and/or second pair of mating surfaces are inclined at an angle with respect to a radial plane of the vane carrier structure,
a retention device for securing the spacer to the vane carrier structure, the retention device comprising a radial retention bolt configured to apply an axial load on the clamp when tightened;
wherein the recess has a circumferential contour that comprises at least a pair of valleys delimiting a radially outward extent of the recess, the valleys being interspaced by a radially inwardly projecting tang, wherein a radially outer end of the clamp has a shape that corresponds to the contour of the recess, whereby the tang provides a circumferential constraint of the transition aft frame to the vane carrier structure.

US Pat. No. 9,627,938

RADIAL LEAD SEAL ASSEMBLY FOR A GENERATOR AND METHOD INCORPORATING THE SAME

SIEMENS ENERGY, INC., Or...

1. A radial lead seal assembly of a generator, wherein the generator comprises a lead assembly for conducting a field current
to a rotor winding, wherein the lead assembly comprises an axial lead extending within an axial chamber through the rotor
and a radial lead extending radially outward from the axial lead through a radial chamber, the radial lead seal assembly comprising:
a plurality of annular sealing elements disposed annularly around the radial lead to seal an annular space between the radial
lead and the radial chamber and thereby seal the axial chamber fluidically from the radial chamber;

a plurality of conical springs disposed annularly around the radial lead between the plurality of sealing elements and a junction
between the radial lead and the axial lead; and

a loading member for exerting a compressive load on the radial lead seal assembly in a radially inward direction such that
the conical springs are only partially compressed,

wherein a clearance from an outer diameter of the conical springs to an inner diameter of the radial chamber is smaller than
a clearance from an inner diameter of the conical springs to an outer diameter of an insulation of the radial lead so that
the conical springs do not contact with an insulated surface of the radial lead.

US Pat. No. 9,500,710

GENERATOR NEUTRAL GROUND MONITORING SYSTEM AND METHOD

SIEMENS ENERGY, INC., Or...

1. A method comprising:
monitoring a voltage waveform across a second winding of a neutral grounding transformer of a three-phase generator, wherein
the three-phase generator comprises a neutral bus bar, and the neutral grounding transformer comprises a primary winding and
the second winding, the primary winding electrically coupling the neutral bus bar to ground;

acquiring a present sample of the voltage waveform;
comparing the present sample to one or more of a plurality of past samples of the voltage waveform;
based on a similarity between the present sample to the one or more past samples, identifying a generator fault associated
with the present sample;

generating an operational control signal for the three-phase generator based on the generator fault.

US Pat. No. 9,427,839

LAPPING TOOL

SIEMENS ENERGY, INC., Or...

1. A lapping tool for lapping sealing surfaces of a fitting used in a gas turbine, comprising:
a shaft having first and second ends and a longitudinal axis;
a removable handle attached to the second end of the shaft; and
first and second removable lapping inserts, each having an outwardly extending attachment portion for attachment to the first
end of the shaft, wherein the lapping inserts each include a lapping surface which corresponds to the shape of a sealing surface
of the fitting and wherein:

the first lapping insert includes a cavity defining a tapered lapping surface for receiving and lapping an exterior surface
of a first portion of the fitting; and

the second lapping insert includes a projection defining a tapered lapping surface for insertion into and lapping an interior
surface in a second portion of the fitting, wherein the second portion of the fitting forms a receptacle portion for sealingly
receiving the first portion of the fitting.

US Pat. No. 9,395,171

CAPACITIVE SENSOR WITH ORTHOGONAL FIELDS

SIEMENS ENERGY, INC., Or...

1. A proximity sensor comprising:
a first pair of electrodes aligned along a first axis;
a second pair of electrodes aligned along a second axis substantially perpendicular to the first axis;
a signal generator configured to apply a first signal across the first pair of electrodes to produce a first electric field
and to apply a second signal across the second pair of electrodes to produce a second electric field that is substantially
perpendicular to the first electric field, wherein the first and second electric fields are produced concurrently;

a detector configured to concurrently detect a first change in the first signal due to an object interacting with the first
electric field and a second change in the second signal due to the object interacting with the second electric field; and

a comparator configured to determine a distance of the object from the first and second pair of electrodes based on a ratio
of the first and second changes.

US Pat. No. 9,366,443

LEAN-RICH AXIAL STAGE COMBUSTION IN A CAN-ANNULAR GAS TURBINE ENGINE

SIEMENS ENERGY, INC., Or...

1. A method for axial stage combustion in a gas turbine engine comprising:
mixing air and fuel to form a lean air-fuel mixture of air and fuel in a first stage of combustion of a can-annular combustor
of the gas turbine engine, wherein the lean air-fuel mixture of air and fuel has an equivalence ratio of less than one;

igniting the lean air-fuel mixture at the first stage of combustion to create hot combustion gas having a first temperature
and free radicals;

disposing an air-fuel mixing arrangement in a second stage of combustion of the can-annular combustor, the second stage of
combustion located downstream from the first stage of combustion, the air-fuel mixing arrangement coupled to receive fuel
delivered in the second stage of combustion by a plurality of fuel nozzles and further coupled to receive a flow of air in
the second stage of combustion;

mixing air and fuel received by the air-fuel mixing arrangement to form a rich air-fuel mixture of air and fuel in the second
stage of combustion, wherein the rich air-fuel mixture of air and fuel has an equivalence ratio of greater than one;

wherein the mixing of air and fuel received by the air-fuel mixing arrangement comprises adjustably varying a volumetric flow
rate of fuel delivered in the second stage of combustion by the fuel nozzles by way of respective valves in each fuel nozzle
to adjustably vary the equivalence ratio of the rich air-fuel mixture,

injecting the rich air-fuel mixture into the second stage of combustion; and
igniting the rich air-fuel mixture in the hot combustion gas at the second stage of combustion, such that the first temperature
and the free radicals of the hot combustion gas promote combustion of the rich air-fuel mixture within a predetermined hydrocarbon
emissions limit, and the first temperature of the hot combustion gas increases to a second temperature.

US Pat. No. 9,359,897

METHOD FOR BUILDING A GAS TURBINE ENGINE COMPONENT

SIEMENS ENERGY, INC., Or...

1. A method, comprising:
providing a layer of powder material on a substrate; and
traversing an energy beam across the layer of powder material to form a cladding layer, wherein the cladding layer forms a
layer of an airfoil, the traversing comprising:

starting a first path and a second path of traversal of the energy beam from a common initiation point;
forming a portion of a first side wall of the cladding layer and a first rib section by traversing the energy beam along the
first path and concurrently forming a portion of a second side wall of the cladding layer by traversing the energy beam along
the second path; and

creating not more than one initiation point for each rib section in the cladding layer;
further comprising removing at least a portion of an airfoil from an existing component, thereby forming the substrate;
forming the first rib section as part of the first path by widening the energy beam to span at least from the first side wall
to the second side wall and traversing the energy beam along a short dimension of the first rib section; and

starting a third path of traversal of the energy beam on the first side wall abutting the first rib section.

US Pat. No. 9,349,516

MULTIDIRECTIONAL MAGNETIC PARTICLE INSPECTION SYSTEM

SIEMENS ENERGY, INC., Or...

1. A magnetic particle inspection system, comprising:
a first magnetizing coil oriented in a first direction, the first magnetizing coil configured as a rectangular spiral located
in a plane;

a second magnetizing coil oriented in a second direction perpendicular to the first orientation, the second magnetizing coil
configured as a rectangular spiral located in a common plane with the first magnetizing coil;

a mat for supporting an article to be inspected, wherein the first and second magnetizing coils are located in the mat;
a power supply for supplying power for energizing the first and second magnetizing coils; and
a switching unit for switching current flow between the first and second magnetizing coils;
wherein the first magnetizing coil includes parallel first and second legs connected by opposing end areas of the first magnetizing
coil and the second magnetizing coil includes parallel third and fourth legs connected by opposing end areas of the second
magnetizing coil and oriented perpendicular to the first and second legs.

US Pat. No. 9,341,462

SENSOR FOR MEASURING BLADE TIP CLEARANCE IN GAS TURBINES

Siemens Energy, Inc, Orl...

1. A proximity sensor for determining a distance between an inner surface of a stationary portion of a turbo machine that
defines a gas flow path and a moving portion of the turbo machine within the gas flow path, comprising:
a fixed gap capacitive probe located within a cavity defined in the stationary portion of the turbo machine and configured
to sense a characteristic of a gas flowing through the gas flow path and to generate a first output signal which varies based
on the characteristic of the gas, the fixed gap capacitive probe having a pair of radially spaced conductive plates wherein
a radially innermost conductive plate is located within the cavity radially outward from the inner surface of the stationary
portion;

a variable gap capacitive probe located within the cavity adjacent the fixed gap capacitive probe, wherein the variable gap
probe is configured to capacitively couple to a moving blade of the turbo machine and to generate a second output signal which
varies based on a distance between the variable gap capacitive probe and the moving blade of the turbo machine; and

a signal processor configured to adjust a value of the second output signal based on the first output signal to produce an
adjusted output signal.