US Pat. No. 9,342,060

ADAPTIVE CONTROL FOR A GAS TURBINE ENGINE

United Technologies Corpo...

1. A method for adaptively controlling a gas turbine engine, comprising:
generating model parameter data as a function of prediction error data, which model parameter data includes at least one model
parameter that accounts for off-nominal operation of the engine and at least one model parameter that accounts for nominal
operation of the engine, wherein the engine is configured for an airplane propulsion system;

at least partially compensating an on-board model for the prediction error data using the model parameter data;
generating model term data using the on-board model, wherein the on-board model includes at least one model term that accounts
for the off-nominal operation of the engine, the model term comprises a mathematical equation, and the model term data comprises
one or more terms of the mathematical equation;

respectively updating one or more model parameters and one or more model terms of a model-based control algorithm with the
model parameter data and model term data; and

generating one or more effector signals using the model-based control algorithm.

US Pat. No. 9,121,367

GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT

United Technologies Corpo...

1. An arrangement for a gas turbine engine comprising:
a fan section having a central axis;
a compressor case for housing a compressor;
an inlet case for guiding air to the compressor, the compressor case positioned axially further from the fan section than
the inlet case;

a support member extending between the fan section and the compressor case wherein the support member restricts movement of
the compressor case relative to the inlet case;

the compressor case includes an upstream compressor case portion and a downstream compressor case portion, the downstream
compressor case portion being axially further from the inlet case than the upstream compressor case portion, wherein the support
member extends between the fan section and the upstream compressor case portion, and the inlet case is removable from the
gas turbofan engine separately from the compressor case;

the compressor case includes a low pressure compressor section and a high pressure compressor section.

US Pat. No. 9,416,673

HYBRID INNER AIR SEAL FOR GAS TURBINE ENGINES

United Technologies Corpo...

1. A turbine section comprising:
first and second turbine rotors each carrying turbine blades for rotation about a central axis, said rotors each having at
least one rotating seal at a radially inner location;

a vane section formed of a plurality of circumferentially spaced vane components, each of said vane components having an airfoil
extending radially outwardly of a platform;

a first seal fixed to said platform, said first seal having a seal material positioned to be adjacent said at least one rotating
seal from the first rotor which is positioned in one axial direction relative to said first seal;

a second seal extending circumferentially beyond at least a plurality of said vane components, said second seal having seal
material positioned to be adjacent said at least one rotating seal of the second rotor on an opposed axial side from said
first rotor, the second seal extends for a greater circumferential extent than does the first seal;

said first and second seals include said seal material mounted onto a seal mount, and wherein said material is more abradable
than a material forming said mount; and

a first arm is fixed to said platform and extends radially inwardly in an opposed direction from said airfoil, with said arm
extending to said seal mount for said first seal, and a second arm extending radially inwardly from platform, with said second
arm including a connection to said mount for said second seal that allows movement.

US Pat. No. 9,453,419

GAS TURBINE ENGINE TURBINE BLADE TIP COOLING

UNITED TECHNOLOGIES CORPO...

1. An airfoil for a gas turbine engine comprising:
pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having
an exterior surface that extends in a radial direction to a tip, a camber line at the tip extending from the leading edge
to the trailing edge;

pressure and suction side shelves arranged in the exterior surface on opposing sides of the camber line respectively in the
pressure and suction walls;

a plateau proud of and separating the pressure and suction side shelves, the plateau arranged along the camber line and extending
from the leading edge to the trailing edge and from the pressure side shelf to the suction side shelf in an airfoil thickness
direction, wherein the plateau is without a tip pocket; and

wherein the airfoil has a cooling passage arranged between the pressure and suction walls that extends toward the tip, and
cooling holes fluidly interconnecting the cooling passage and the pressure and suction side shelves, wherein at least one
of the pressure side shelf and the suction side shelf is spaced from the leading edge.

US Pat. No. 9,297,312

CIRCUMFERENTIALLY RETAINED FAIRING

United Technologies Corpo...

6. An assembly for a gas turbine engine, comprising:
a frame;
a strut extending from the frame;
a mount attached to the frame, the mount comprising:
a ring extending around an engine centerline and having one or more slots therein, wherein each slot has side walls extending
in a radial direction relative to the frame and an end wall joining the side walls; and a fairing that defines a gas flow
path for the gas turbine engine, wherein the fairing is disposed around the strut and has a first fixed connection to the
frame and a second connection to the frame, and wherein the second connection allows for both radial and axial movement of
the fairing relative to the frame while preventing circumferential movement of the fairing relative to the frame, and wherein
the second connection comprises:

one or more lugs extending from the fairing, wherein each lug has mating walls extending in a substantially axial direction
relative to the frame, each mating wall disposed opposite one of the side walls of one of the slots, and wherein the one or
more lugs are received in the one or more slots.

US Pat. No. 9,080,452

GAS TURBINE ENGINE AIRFOIL WITH VANE PLATFORM COOLING PASSAGE

UNITED TECHNOLOGIES CORPO...

1. A stator vane for a gas turbine engine comprising:
an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface, a cooling passage arranged
in the platform and including a circumferential passage fluidly connected to an inlet passage extending through an edge of
the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radically extending
passage through the edge of the platform, and a void interconnected to at least one of the radially extending passage and
the inlet passage.

US Pat. No. 9,382,807

NON-AXISYMMETRIC RIM CAVITY FEATURES TO IMPROVE SEALING EFFICIENCIES

United Technologies Corpo...

1. Turbomachinery comprising:
a first part having a first surface and a second part having a second surface, each of said first and second surfaces are
an axial surface, and each said axial surface parallels a centerline of said turbomachinery, wherein said first surface and
said second surface both rotate;

a cavity between said first and second surfaces;
said first surface moving relative to said second surface; and
at least one non-axisymmetric three dimensional feature which extends outwardly into said cavity in both the circumferential
and radial directions from said first and second surfaces.

US Pat. No. 9,410,608

FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE

UNITED TECHNOLOGIES CORPO...

1. A geared architecture for a gas turbine engine comprising:
a fan shaft;
a frame which supports said fan shaft, said frame defines a frame stiffness;
a plurality of gears which drives said fan shaft;
a flexible support which supports the geared architecture and defines a flexible support stiffness that is less than said
frame stiffness; and

an input coupling to said plurality of gears, said input coupling defines an input coupling stiffness which is less than said
frame stiffness, wherein said flexible support stiffness and said input coupling stiffness are each less than about 20% of
said frame stiffness.

US Pat. No. 9,297,314

GAS TURBINE ENGINE WITH ACCESSORY GEAR BOX

United Technologies Corpo...

1. A nacelle for incorporation into a gas turbine engine, comprising:
a nacelle having an inner wall defining a bypass duct, and an outer wall, at least one drive shaft extending through said
inner wall, said at least one drive shaft to be connected to a gas turbine engine receiving the nacelle, said at least one
drive shaft being connected to drive at least two accessory gear boxes, with said at least two accessory gear boxes being
received between said inner and outer walls of said nacelle; and

said at least two accessory gearboxes being circumferentially spaced; and
said at least one drive shaft consists of one drive shaft driving both of said at least two accessory gearboxes via a first
split shaft and a second split shaft within the nacelle.

US Pat. No. 9,267,389

GEARED ARCHITECTURE CARRIER TORQUE FRAME ASSEMBLY

United Technologies Corpo...

16. A method of assembling a fan drive gear system for a gas turbine engine comprising:
inserting a shelf extending between gear mount sections of a carrier into a space defined between two ends of a finger section
extending from a torque frame; and

inserting a pin through openings defined in the two ends of the finger section and the shelf.

US Pat. No. 9,297,335

METAL INJECTION MOLDING ATTACHMENT HANGER SYSTEM FOR A COOLING LINER WITHIN A GAS TURBINE ENGINE SWIVEL EXHAUST DUCT

UNITED TECHNOLOGIES CORPO...

1. An exhaust duct assembly for a gas turbine engine comprising:
an exhaust duct case segment;
a cooling liner segment; and
an attachment hanger system attachable between said exhaust duct case section and said cooling liner segment, said attachment
hanger system having at least one component manufactured by metal injection molding (MIM).

US Pat. No. 9,228,438

VARIABLE VANE HAVING BODY FORMED OF FIRST MATERIAL AND TRUNNION FORMED OF SECOND MATERIAL

United Technologies Corpo...

1. A variable vane comprising:
a variable vane body including an airfoil portion, the variable vane body being formed of a first material; and
a trunnion attached at one end of the variable vane body, the trunnion including a pivot formed of a second, different material,
wherein the first material has a first density and the second material has a second density that is greater than the first
density.

US Pat. No. 9,133,713

GAS TURBINE ENGINE TURBINE BLADE AIRFOIL PROFILE

UNITED TECHNOLOGIES CORPO...

1. A turbine blade for a gas turbine engine comprising:
an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil
surface extending from a platform in a radial direction to a tip; and

wherein the external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil
described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate
scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location, wherein the
local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.

US Pat. No. 9,297,270

GAS TURBINE ENGINE DRIVING MULTIPLE FANS

United Technologies Corpo...

1. A gas turbine engine comprising:
a core engine including a compressor section, a combustor and a turbine, said turbine driving an output shaft;
said output shaft driving at least four gears, each of said at least four gears extending to a separate drive shaft to drive
an associated one of at least four fan rotors; and

said separate drive shafts each extending from one of said at least four gears to drive a fan drive shaft which in turn drives
said associated fan rotor; wherein said output of said core engine drives a pair of bevel gears, and each of said at least
four gears being driven by at least one of said pair of bevel gears.

US Pat. No. 9,394,793

TURBOMACHINE BLADE

United Technologies Corpo...

1. A turbomachine airfoil element comprising:
an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side,
wherein:
a span between the inboard end and the outboard end is 1.4-1.6 inch;
a chord length at 50% span is 0.9-1.4 inch; and
at least three of:
a first mode resonance frequency is 2591.5±10% Hz;
a second mode resonance frequency is 4675.2±10% Hz;
a third mode resonance frequency is 7892.9±10% Hz;
a fourth mode resonance frequency is 10098.2±10% Hz; and
a fifth mode resonance frequency is 14808.2±10% Hz.

US Pat. No. 9,422,819

ROTOR BLADE ROOT SPACER FOR ARRANGING BETWEEN A ROTOR DISK AND A ROOT OF A ROTOR BLADE

United Technologies Corpo...

1. A rotor assembly, comprising:
a rotor disk including a slot;
a rotor blade including a blade root arranged within the slot, the blade root including a root base segment and a pair of
root side segments, wherein the root base segment is laterally separated from the rotor disk by the root side segments; and

a root spacer arranged within the slot, the root spacer including a side surface that extends radially between an inner surface
and an outer surface, wherein

the side surface is approximately laterally aligned with an intersection between the root base segment and a first of the
root side segments; and

the outer surface engages the root base segment;
wherein the root spacer includes a spacer base segment and a spacer side segment;
wherein the spacer base segment is arranged radially between the root base segment and the rotor disk; and
wherein the spacer side segment is arranged radially between a second of the root side segments and the rotor disk.

US Pat. No. 9,394,613

PROCESSES FOR APPLYING A CONVERSION COATING WITH CONDUCTIVE ADDITIVE(S) AND THE RESULTANT COATED ARTICLES

United Technologies Corpo...

1. A process for providing a conversion coating on an aluminum alloy article, comprising:
contacting an article with a first solution to produce a coated article, said first solution includes a solvent and at least
one non-conductive material comprising at least one oxide of a metal, and said coated article having at least one surface
with a layer of said non-conductive material;

contacting said coated article with a second solution which includes a solvent and at least one conductive material comprising
at least one of: graphite, metals, conductive ceramics, semi-conductive ceramics, intermetallic compounds, and mixtures thereof,
thereby producing a further coated article having said layer on said at least one surface and having said at least one conductive
material in contact with said layer and said at least one surface; and

drying said further coated article to produce a dried coated article having a conversion coating on said at least one surface,
said conversion coating having said layer on said at least one surface and said at least one conductive material in contact
with said layer and said at least one surface, wherein the drying takes place at a temperature of between 25° C. and 125°
C., wherein during the step of contacting said coated article with a second solution, the conductive material from the second
solution infiltrates pores of the layer of said non-conductive material to reach the at least one surface.

US Pat. No. 9,322,285

LARGE FILLET AIRFOIL WITH FANNED COOLING HOLE ARRAY

United Technologies Corpo...

1. A gas turbine engine component comprising:
an airfoil extending through a radial extent, and having a nominal portion with a fillet merging into an end wall and a circumferential
dimension defined between opposed side walls;

said fillet extending over a radial extent of greater than 5% of said radial extent of the airfoil; and
cooling holes formed in said nominal portion and in said fillet, said cooling holes in said nominal portion extending for
a first circumferential extent, and said cooling holes in said fillet extending for a second circumferential extent that is
greater than said first circumferential extent.

US Pat. No. 9,260,973

FAN BLADE ADJUSTMENT PIEZOELECTRIC ACTUATOR

United Technologies Corpo...

1. A system comprising:
a transmission to be rotated to change a pitch angle of a plurality of airfoils;
said transmission being driven through a rotating input to in turn rotate, and change the angle;
said input being caused to rotate by a piston having threads engaging threads on said input, and said piston being mounted
within a hydraulic housing, and having opposed chambers on each of two opposed ends of said piston; and

a piezoelectric pump for selectively delivering fluid into said opposed chambers to drive said piston, and to in turn cause
said input to rotate.

US Pat. No. 9,420,595

COMMUNICATION OF AVIONIC DATA

United Technologies Corpo...

1. An avionic data communication method comprising:
determining one or more available communication channels within a plurality of communication channels;
selecting one of the plurality of available communication channels using a channel controller, the channel controller configured
to determine a quality of service of the available communication channels and to select one of the plurality of available
communication channels having a cost threshold value that is not less than the cost threshold value of another channel within
the plurality of available communication channels; and

communicating data between an aircraft and a ground-based system using the selected one of the plurality of available channels,
wherein the cost threshold value changes in response to changes in position of the aircraft relative to the ground-based system.

US Pat. No. 9,322,337

AERODYNAMIC INTERCOMPRESSOR BLEED PORTS

United Technologies Corpo...

1. An air bleed system for a gas turbine engine, comprising:
an annular bleed case having a forward section, an aft section, ligaments spanning between and connecting an inner surface
of the forward section to an inner surface of the aft section, and a series of bleed ports defined by the inner surface of
the forward section, the inner surface of the aft section and the ligaments;

a bleed valve mounted to the annular bleed case; and
a manifold disposed radially outward of the ligaments and extending circumferentially about a circumference of the annular
bleed case, wherein the manifold is formed between the inner surface of the forward section, the inner surface of the aft
section and an outer radial surface of the ligaments, the manifold communicating with the series of bleed ports and allowing
circumferential flow between each one of the series of bleed ports, and wherein the manifold is constructed such that the
manifold is disposed radially inward of the bleed valve when the bleed valve is in a closed position.

US Pat. No. 9,228,533

FLEXIBLE SEAL FOR GAS TURBINE ENGINE SYSTEM

United Technologies Corpo...

1. A flexible seal for use in a gas turbine engine system, comprising:
a flexible annular wall having a first end that is attachable to a gas turbine engine and a second end that is attachable
to a nozzle exhaust, wherein the flexible annular wall comprises a first corrugate section including a first flange and a
second corrugate section including a second flange mechanically secured against the first flange;

wherein the flexible annular wall comprises an elastomer composite having reinforcement fibers disposed within an elastomer
matrix;

wherein the reinforcement fibers comprise glass fibers and the elastomer matrix comprises silicone.

US Pat. No. 9,194,734

LIQUID LEVEL SENSOR SYSTEM

United Technologies Corpo...

1. A method of replenishing liquid in a reservoir, the method comprising the following steps:
sensing temperature of first and second temperature sensors at a first time, wherein the first and second temperature sensors
are positioned at a full level and an add level of the reservoir, respectively;

heating the first and second temperature sensors;
terminating heating of the first and second temperature sensors;
sensing temperature of the first and second temperature sensors at a second time after heating the first and second temperature
sensors;

adding liquid to the reservoir if temperature sensed by the first temperature sensor is different at the first and second
times and if temperature sensed by the second temperature sensor is different at the first and second times and if the first
and second temperature sensors are deemed to be reliable;

repeating all of the above steps until the temperature sensed by the first temperature sensor is the same at the first and
second times and if temperature sensed by the second temperature sensor is the same at the first and second times;

terminating adding of liquid if temperature sensed by the first temperature sensor is the same at the first and second times
and if temperature sensed by the second temperature sensor is the same at the first and second times;

sending an estimated liquid level signal with a value estimated based upon elapsed operating time since liquid in the reservoir
was at or above the full level if the first and second temperature sensors are deemed to be unreliable; and

adding liquid to the reservoir in response to the estimated liquid level signal.

US Pat. No. 9,371,738

VARIABLE OUTER AIR SEAL SUPPORT

United Technologies Corpo...

1. A variable outer air seal support system, comprising:
a case having plurality of slots;
an extension of a variable outer air seal segment, the extension providing at least one extension aperture;
a connector pin extending through both one of the plurality of slots and the at least one extension aperture, the connector
pin configured to move within the slot to move the variable outer air seal segment from a first position to a second position,
the variable outer air seal segment overlapping a circumferentially adjacent variable outer air seal segment more in the first
position than in the second position; and

a link having a first end and a second end that is opposite the first end, the first end providing at least one link aperture
that receives the connector pin, the second end configured to engage another connector pin associated with a circumferentially
adjacent variable outer air seal.

US Pat. No. 9,394,802

SENSOR HOOP STORAGE AND TRANSPORT APPARATUS

United Technologies Corpo...

1. A hoop support device (202) for supporting a hoop assembly (100), the hoop assembly comprising a structural hoop (102) and a plurality of wires, the hoop support device comprising:
a pedestal (206) comprising:

a mounting feature (224, 226) for mounting the hoop;

a base (210) having a plurality of mounting holes (211); and

a web (240) extending upward from the base and bearing the mounting feature and a feature (282) for said pivotal mounting of the cover; and

a cover (208) pivotally mounted to the pedestal for rotation about a pivot axis (510), the cover having at least a lateral portion (250, 252) and a peripheral portion (254) for enclosing at least one said wire in an installed/closed condition.

US Pat. No. 9,267,434

HEAT EXCHANGER

United Technologies Corpo...

7. A gas turbine engine comprising:
a fan duct having a bypass air flow;
a bleed air system for bleeding a bleed air flow from a compressor section into a bleed air chamber, wherein the bleed air
flow is selectively bled from the compressor section into the bleed air chamber;

a heat exchanger having a first convective cooling feature and a second convective cooling feature on a heat exchanger wall,
wherein the first convective cooling feature is disposed on a radially outer side of the heat exchanger wall and at least
partially in fluid communication with the bypass air flow of the gas turbine engine, wherein the second convective cooling
feature is disposed on a radially inner side of the heat exchanger wall and at least partially in the bleed air chamber of
the gas turbine engine and at least partially in fluid communication with the bleed air flow, wherein said heat exchanger
wall separates the bypass air flow from the bleed air flow;

and said heat exchanger selectively cooling a lubricating fluid associated with a generator.

US Pat. No. 9,353,628

GAS TURBINE ENGINE AIRFOIL

UNITED TECHNOLOGIES CORPO...

1. An airfoil for a turbine engine comprising:
an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path
location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a leading edge dihedral
and a span position, the leading edge dihedral negative from the 0% span position to the 100% span position, wherein a positive
dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.

US Pat. No. 9,353,643

VARIABLE STATOR VANE ASSEMBLY FOR A TURBINE ENGINE

UNITED TECHNOLOGIES CORPO...

1. A stator assembly for a turbine engine comprising:
an outer case providing a bore;
a non-metallic bushing arranged in the bore in an interference fit relationship and extending radially between inner and outer
diameters, the outer diameter engaging the bore;

a stator including a trunnion arranged within and engaging the bushing inner diameter;
wherein the trunnion is an outer trunnion received within the bore;
wherein the outer case provides a boss having the bore and extending away from the stator in an axial direction of the bore;
and

wherein the outer case provides a recess defining a wall surface, and the bore extends radially outwardly from the recess
of the outer case.

US Pat. No. 9,297,367

COMBINED GEOTHERMAL AND SOLAR THERMAL ORGANIC RANKINE CYCLE SYSTEM

UNITED TECHNOLOGIES CORPO...

1. An energy recovery system for use with a geothermal source containing a fluid which can be removed at a higher temperature
and returned at a lower temperature, comprising:
an organic rankine cycle system having a closed loop circuit with a working fluid being circulated therethrough;
at least one heat exchanger fluidly connected to said organic rankine cycle system and to be connected to a geothermal fluid
for selectively transferring heat from the geothermal fluid to said organic rankine cycle system;

a solar collector thermally coupled to said at least one heat exchanger for selectively transferring heat from said solar
collector to said organic rankine cycle system; and

a control for controlling the energy recovery system, said control determining whether solar heat is available from said solar
collector, and if heat is available from said solar collector, determining whether sufficient solar heat is available to provide
energy recovery without heat from the geothermal fluid, and operating in a solar mode alone if there is sufficient solar heat
available, operating in a geothermal mode only if there is no solar heat available, and operating in combination of the solar
and geothermal modes if there is solar heat available, but it is not sufficient.

US Pat. No. 9,267,386

FAIRING ASSEMBLY

United Technologies Corpo...

1. A fairing assembly comprising:
an outer wall;
a first side wall and a second side wall extending from opposing sides of the outer wall, wherein together the first side
wall, the second side wall, and the outer wall form a cavity within the fairing assembly; and

a saddle disposed within the cavity and extending between the first side wall and the second side wall, wherein the saddle
has a first linkage adapted to connect to the first side wall and a second linkage adapted to connect to the second side wall,
and wherein the first linkage and the second linkage extend from a central hub.

US Pat. No. 9,145,775

TAPERED THERMAL COATING FOR AIRFOIL

United Technologies Corpo...

1. An airfoil comprising:
pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to
a tip section, the root section and the tip section defining a span therebetween; and

a thermal coating extending from the root section of the airfoil toward the tip section of the airfoil, wherein a relative
coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared
to a relative coating thickness at minimum span in the root section.

US Pat. No. 9,410,445

CASTABLE HIGH TEMPERATURE ALUMINUM ALLOY

United Technologies Corpo...

1. A turbine engine comprising:
an engine core passage and an engine bypass passage defined by a bypass passage outer case extending around the engine core
passage;

a cast fan situated at an inlet of the engine bypass passage such that rotation of the cast fan moves air through the engine
bypass passage;

a compressor within the engine core passage;
a combustor in fluid communication with the compressor; and
a turbine within the engine core passage and in fluid communication with the combustor, the turbine being operative to drive
the cast fan,

wherein the cast fan includes an airfoil made of an aluminum-rare earth element alloy, and the aluminum-rare earth element
alloy has a composition of approximately 1.0 to 20.0% by weight of a first rare earth element selected from a group consisting
of ytterbium and gadolinium, approximately 0.1 to 10.0% by weight of at least one second rare earth element selected from
a group consisting of gadolinium, erbium and yttrium if said first rare earth element is ytterbium or a group consisting of
ytterbium, erbium and yttrium if said first rare earth element is gadolinium and a balance of aluminum, and a plurality of
insoluble particles of aluminum and the first rare earth element.

US Pat. No. 9,464,655

PUSH-LOCK PIN

United Technologies Corpo...

1. A push-lock pin for connecting a plate to a surface comprising:
a cylindrical pin housing;
a shaft within said cylindrical pin housing wherein said shaft comprises a ball-lock mechanism, and a push-down pop-up mechanism;
a cap, connected to a first axial end of said shaft;
a spring connected to a second axial end of said shaft, wherein said second axial end is opposite said first axial end;
wherein said push-down pop-up mechanism comprises a separate pin component, the separate pin component including at least
a portion normal to an axis defined by the shaft and a cam having a first equilibrium point and a second equilibrium point,
wherein said spring is maintained in a compressed state when said cam is at the second equilibrium point, and said spring
is maintained in a partially relaxed state when said cam is at the first equilibrium point;

the separate pin component extends radially into said cam; and
the cam defining a first movement track of the separate pin component from the first equilibrium point to the second equilibrium
point, and a second movement track of the separate pin component from the second equilibrium point to the first equilibrium
point, wherein the first movement track is distinct from the second movement track.

US Pat. No. 9,429,103

VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION

United Technologies Corpo...

1. A method of controlling flutter of a fan nozzle, the method comprising:
providing a fan nozzle having an airfoil cross-sectional shape,
wherein the airfoil cross-sectional shape includes a pressure side wall radially spaced apart from a suction side wall,
wherein at least one of the pressure side wall and the suction side wall has a wall thickness distribution formed by a multi-layered
structure,

determining a vibration frequency and a strain mode that would cause the fan nozzle to flutter, wherein the flutter would
cause high stresses at one or more locations of the at least one of the pressure side wall and the suction side wall; and

reducing the high stresses at the one or more locations by establishing the wall thickness distribution to include multi-layered
local thick portions and multi-layered local thin portions of the least one of the pressure side wall and the suction side
wall that alter the vibration frequency and the strain mode of the fan nozzle.

US Pat. No. 9,284,844

GAS TURBINE ENGINE COMPONENT WITH CUSPED COOLING HOLE

United Technologies Corpo...

1. A component for a gas turbine engine, the component comprising:
a wall having a first surface and a second surface and defining a cooling hole, the cooling hole extending through the wall
from an inlet located at the first wall surface to an outlet located at the second wall surface and having:

a metering section extending from the inlet to a transition;
a diffusing section extending from the transition to the outlet;
a cusp on the transition; and
two longitudinal ridges that divide the diffusing section into three lobes, wherein the cusp bifurcates into the two longitudinal
ridges.

US Pat. No. 9,181,815

SHAPED RIM CAVITY WING SURFACE

United Technologies Corpo...

1. A turbomachine comprising:
a stationary portion;
a rotating portion;
a rim cavity region defined between the stationary portion and the rotating portion; and
a shaped rim cavity wing extending from either the stationary portion or the rotating portion into the rim cavity region,
the shaped rim cavity wing including:

an upper surface;
a lower surface having a geometric shape to control separation of airflow as it passes around the lower surface to the top
surface, the geometric shape including:

a first concave portion;
a convex portion adjacent the first concave portion;
a first inflection point between the convex portion and the first concave portion;
a second concave portion adjacent the convex portion; and
a second inflection point between the second concave portion and the convex portion; and
a point of maximum extent that defines a boundary between the upper surface and the lower surface, wherein the point of maximum
extent defines a corner that separates airflow from the shaped rim cavity wing and creates flow re-circulation adjacent to
the upper surface of the shaped rim cavity wing;

wherein the first concave portion is located adjacent the point of maximum extent.
US Pat. No. 9,382,605

ECONOMIC OXIDATION AND FATIGUE RESISTANT METALLIC COATING

United Technologies Corpo...

1. A method for depositing an overlay coating on a substrate comprising:
providing a substrate material formed from at least one of a nickel-based, a cobalt-based, and an iron-based metallic material;
and

depositing onto the substrate a coating having a composition consisting of 1.0 to 18 wt % cobalt, 3.0 to 18 wt % chromium,
5.0 to 15 wt % aluminum, 0.01 to 1.0 wt % yttrium, 0.01 to 0.6 wt % hafnium, 0.0 to 0.3 wt % silicon, 0.1 to 1.0 wt % zirconium,
0.0 to 10 wt % tantalum, 2.5 to 5.0 wt % tungsten, 0.0 to 10 wt % molybdenum, 23.0 to 27.0 wt % platinum, and the balance
nickel.

US Pat. No. 9,260,972

TIP LEAKAGE FLOW DIRECTIONALITY CONTROL

United Technologies Corpo...

1. A turbine airfoil comprising:
a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise
between a leading edge and a trailing edge;

a tip wall extending chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the
suction and pressure sidewalls; and

a plurality of tip leakage control channels distributed across at least a chordwise portion of the tip wall between the airfoil
leading edge and the airfoil trailing edge, each channel recessed into an outer surface of the tip wall, an inlet of each
channel beginning proximate a junction of the airfoil pressure sidewall and the tip wall, an outlet of each channel terminating
at a recessed portion of a junction of the tip wall and the suction sidewall, and a portion of each channel curved toward
the trailing edge from the inlet to the outlet.

US Pat. No. 9,127,334

DIRECT FORGING AND ROLLING OF L12 ALUMINUM ALLOYS FOR ARMOR APPLICATIONS

United Technologies Corpo...

1. A method for producing high strength aluminum alloy armor plate containing L12 dispersoids, comprising the steps of:
forming a powder containing L12 dispersoids in a matrix consisting of 4-25 weight percent silicon and the balance substantially aluminum, wherein the L12 dispersoids comprise:

A13X dispersoids wherein X is at least one first element selected from the group consisting of about 0.1 to about 15.0 weight
percent thulium, about 0.1 to about 25.0 weight percent ytterbium, and about 0.1 to about 25.0 weight percent lutetium; and
at least one second element selected from the group consisting of about 0.1 to about 20.0 weight percent gadolinium, about
0.1 to about 20.0 weight percent yttrium, and about 0.05 to about 10.0 weight percent hafnium;

consolidating the powder into a billet with a rectangular cross-section having a density of about 100 percent; and
hot working the billet to redistribute oxides throughout the microstructure, to provide additional Orowan barriers to deformation,
and to reduce thickness to form armor plate having a yield strength and tensile strength in excess of 75 ksi (517 MPa).

US Pat. No. 9,068,629

FAN DRIVE PLANETARY GEAR SYSTEM INTEGRATED CARRIER AND TORQUE FRAME

UNITED TECHNOLOGIES CORPO...

1. A fan gear drive system comprising:
a fan shaft;
a turbine shaft;
a fixed structure; and
a gear train including:
a torque frame comprising a base with integrated gear shafts circumferentially spaced relative to one another, and each gear
shaft providing a gear shaft axis,

a central gear located radially inward from and intermeshing with intermediate gears, each intermediate gear mounted on a
respective gear shaft and configured to rotate about its respective gear shaft axis,

a ring gear arranged about and intermeshing with the intermediate gears, and
wherein one of the torque frame, central gear and ring gear is connected to the fan shaft, another of the torque frame, central
gear and ring gear is connected to the turbine shaft, and a remaining of the torque frame, central gear and ring gear is connected
to the fixed structure; and

a bearing assembly is mounted on each of the gear shafts and provides a bearing axis, each bearing assembly supports one of
the respective intermediate gears.

US Pat. No. 9,410,446

DYNAMIC STABILITY AND MID AXIAL PRELOAD CONTROL FOR A TIE SHAFT COUPLED AXIAL HIGH PRESSURE ROTOR

UNITED TECHNOLOGIES CORPO...

1. A turbine engine, comprising:
a first bearing on a first end of a unitary tie shaft;
an upstream hub threadably engaged with the tie shaft;
a compressor rotor stack supported by and operatively associated with the tie shaft and abutting the upstream hub;
a middle support member abutting the compressor rotor stack, the middle support member having a downstream hub and a soft
spring kickstand;

a high pressure compressor coupling nut abutting the soft spring kickstand and threadably engaged with the tie shaft;
a turbine rotor stack operatively associated with the tie shaft and abutting the downstream hub;
a turbine rotor arm operatively associated with the turbine rotor stack and interferingly fitting with the tie shaft;
a high pressure turbine lock nut threadably engaged with the tie shaft and abutting the turbine rotor arm;
an intermediary sleeve interferingly fitting with the turbine rotor arm;
a second bearing having inner and outer races, the inner race interferingly fitting with an outside diameter of the intermediary
sleeve; and

a downstream lock nut threadably engaged with the tie shaft and abutting the high pressure turbine lock nut.

US Pat. No. 9,377,198

HEAT SHIELD FOR A COMBUSTOR

United Technologies Corpo...

23. A gas turbine engine comprising:
a compressor section;
an annular combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the annular combustor, the annular combustor including an annular outer shell
and an annular inner shell radially inwardly spaced from the annular outer shell to define an annular combustion chamber there
between, an annular hood secured to the annular outer shell and the annular inner shell, a bulkhead secured to the annular
combustion chamber and the annular hood, and an annular heat shield mounted in the combustion chamber on the bulkhead, the
annular heat shield including:

a plurality of panels, each of the plurality of panels including a forward face and an aft face, a circumferential outer side
and a circumferential inner side, the circumferential outer side facing radially outwards and the circumferential inner side
facing radially inwards, an opening extending between the forward face and the aft face, a lip projecting from the forward
face and extending around the opening, a rail projecting from the forward face adjacent to a periphery of the plurality of
panels and substantially enclosing the lip to define a cavity region between the lip and the rail, and a plurality of holes
in the cavity region, each of the plurality of holes extending from the forward face to the aft face, a portion of the holes
located toward the circumferential outer side are sloped radially outwards from the forward face to the aft face at an angle
of less than 80° with respect to the aft face to provide an air curtain thermally protecting the circumferential outer side,
and a radial region of the annular heat shield extending from the plurality of lips to the circumferential outer side is free
of any aft-projecting features.

US Pat. No. 9,291,123

GAS TURBINE ENGINE EXHAUST DUCT

United Technologies Corpo...

1. An exhaust duct for a gas turbine engine comprising:
an inner wall and an outer wall connected by a plurality of spaced ribs, said duct extending axially, and the ribs extending
circumferentially across an entire cross-section of the inner and outer walls, and said plurality of ribs being spaced axially
along the exhaust duct; and

said inner wall having an inner surface facing an inner chamber, and said inner surface receiving a coating, with said coating
deposited on a metal wire fiber strain isolation pad which is connected to said inner surface.

US Pat. No. 9,260,629

HYDROPHOBIC COATING FOR COATED ARTICLE

United Technologies Corpo...

1. A coated article comprising:
a substrate; and
a superhydrophobic coating on the substrate, and the superhydrophobic coating is a composite of a silicone polymer and particles
that are hydrophobic or surface-functionalized with a hydrophobic agent, wherein the particles are nanosized silica particles,
and the superhydrophobic coating includes a mass ratio of the silicone polymer to the particles that is 0.5-3.

US Pat. No. 9,097,211

SLIDEABLE LINER ANCHORING ASSEMBLY

United Technologies Corpo...

16. A method of securing an engine liner comprising:
(a) positioning an engine liner within an engine casing in a first position;
(b) sliding a liner anchoring structure relative the liner and the casing within a guide defined by at least one of the liner
and the casing; and

(c) securing the liner in the first position during the sliding by moving the liner anchoring structure from a disengaged
position within the guide to an engaged position within the guide.

US Pat. No. 9,068,515

ACCESSORY GEARBOX WITH TOWER SHAFT REMOVAL CAPABILITY

United Technologies Corpo...

1. An accessory system for a gas turbine engine comprising:
an accessory gearbox which defines an accessory gearbox axis, the accessory gearbox including a first side and a second side;
a first geartrain within the accessory gearbox including one or more shafts rotatable about axes perpendicular to the first
side of the accessory gearbox;

a second geartrain within the accessory gearbox including one or more shafts rotatable about axes perpendicular to the second
side of the accessory gearbox;

a driven gear set defining an input axis;
a first drive gear set driven by the driven gear set about a first drive axis for driving the first geartrain; and
a second drive gear set driven by the driven gear set about a second drive axis for driving the second geartrain,
wherein the first drive axis and the second drive axis are substantially parallel to the input axis.

US Pat. No. 9,051,847

FLOATING SEGMENTED SEAL

United Technologies Corpo...

1. A gas turbine engine rotor section comprising:
a rotor body, said rotor body having a ledge extending axially from a location on said rotor body;
said ledge defining a radially inner surface radially inwardly of said ledge, and a hub extending axially from said rotor,
said hub extending to a downstream rotor body, and beyond said ledge, said hub having a radially outer surface spaced from
said ledge radially inner surface, and a first distance defined between said radially inner surface of said ledge and said
radially outer surface of said hub; and

a knife edge seal, said knife edge seal having at least one pointed knife seal portion at a radially outer end, a radially
inwardly extending arm, and an axially inwardly extending portion extending axially inwardly from said radially inwardly extending
arm, said axially inwardly extending portion having a radially outer face and a radially inner face, and said radially inner
and radially outer faces of said knife edge seal being spaced by a second distance, with said second distance being less than
said first distance, and said axially inwardly extending portion being received between said radially inner surface of said
rotor and said radially outer surface of said hub, such that said knife edge seal is free floating between said ledge and
said hub.

US Pat. No. 9,410,556

RING SEAL MIDPLATE

UNITED TECHNOLOGIES CORPO...

1. A seal assembly for a rotary machine which includes a rotor assembly having a rotatable rotor shaft, the seal assembly
being disposed to restrict a leakage of a lubricating fluid from a bearing compartment of the rotary machine and an entry
of a hot working medium gas into the bearing compartment, the seal assembly comprising:
a spacer which is rotatable with the rotor shaft and which extends circumferentially about and radially outward from the rotor
shaft;

a seal plate which is rotatable with the rotor shaft and which extends circumferentially about and radially outward from the
rotor shaft, the seal plate including a longitudinally extending leg and a radially outwardly extending leg extending from
the longitudinally extending leg;

a ring seal which is free and which is longitudinally located between the spacer and the seal plate and radially spaced between
a stationary housing liner and the rotor shaft, a seal plate-facing surface of the ring seal abutting the seal plate at a
radially extending seal plate region of the seal plate and slidably engaging the seal plate, a housing liner-facing surface
of the ring seal abutting the stationary housing liner at a circumferentially extending housing liner region of the stationary
housing liner and in slidable or static engagement with the stationary housing liner; and

a ring seal midplate which is rotatable with the rotor shaft and which extends circumferentially about and radially outward
from the rotor shaft, wherein the ring seal midplate is not attached to the spacer or the seal plate during a hardface process
which is applied to any component of the seal assembly, and wherein the ring seal midplate is longitudinally located between
the spacer and the longitudinally extending leg of the seal plate and radially spaced between the ring seal and the rotor
shaft.

US Pat. No. 9,335,049

COMBUSTOR LINER WITH REDUCED COOLING DILUTION OPENINGS

United Technologies Corpo...

1. A combustor liner for a gas turbine engine, the combustor liner being arcuate in shape and defining an axis and a circumferential
direction, the combustor liner comprising:
a first row of dilution openings in the liner, the first row of dilution openings running in the circumferential direction;
and

a second row of dilution openings in the liner, the second row of dilution openings running parallel to the first row of dilution
openings and axially spaced from the first row of dilution openings; each dilution opening of the second row of dilution openings
at least partially overlapping in an axial direction a portion of each of two adjacent dilution openings of the first row
of dilution openings; and

wherein the dilution openings are substantially rectangular.

US Pat. No. 9,291,071

TURBINE NOZZLE BAFFLE

United Technologies Corpo...

1. A turbine nozzle baffle including an annular box structure, the baffle comprising:
a first diaphragm extending from an inner diameter of the annular box structure to an outer diameter of the annular box structure
to form a first axial side and including a flange projecting radially outward from the outer diameter of the annular box structure
at the first axial side;

a second diaphragm, a first portion of the second diaphragm extending from the inner diameter to the outer diameter to form
a second axial side, the second axial side spaced apart from the first axial side in an axial direction; a second portion
of the second diaphragm extending toward the first axial side to form the outer diameter of the annular box structure; the
second diaphragm connected to the first diaphragm at the outer diameter;

a static portion of a rotating seal facing radially inward at the inner diameter between the first axial side and the second
axial side; and

an interference fit ring connected to the outer diameter of the annular box structure at the second axial side;
wherein the first diaphragm, the second diaphragm, and the static portion of the rotating seal are connected together to form
the annular box structure.

US Pat. No. 9,375,782

REGENERATING AN ADDITIVELY MANUFACTURED COMPONENT

United Technologies Corpo...

9. A method to regenerate a component with internal passageways, the method comprising:
additively manufacturing the component to have voids greater than 0 percent but less than approximately 15 percent by volume
with an internal passageway in a near finished shape;

filling the internal passageway with a slurry;
curing the slurry to form a core;
encasing the component in a shell mold;
curing the shell mold;
placing the encased component in a furnace and melting the component;
solidifying the component in the shell mold; and
removing the shell mold and core from the solidified component.

US Pat. No. 9,376,926

GAS TURBINE ENGINE FAN BLADE LOCK ASSEMBLY

UNITED TECHNOLOGIES CORPO...

1. A gas turbine engine fan blade lock assembly comprising:
a fan hub having blade slots each configured to receive a root of a fan blade, the fan hub including circumferentially spaced
first slots;

a lock ring configured to move between unlocked and locked positions, the lock ring including circumferentially spaced second
slots aligned with the first slots in the locked position; and

multiple discrete pins, each pin configured to be slidably received in paired first and second slots that provide a radial
gap there between in the locked position to prevent rotational movement of the lock ring relative the fan hub, the pin engaging
the lock ring and the fan hub at the radial gap in an interference fit.

US Pat. No. 9,359,906

ROTOR BLADE ROOT SPACER WITH A FRACTURE FEATURE

United Technologies Corpo...

1. A rotor assembly, comprising:
a rotor disk including a slot;
a rotor blade including a blade root arranged within the slot; and
a root spacer arranged within the slot between the rotor disk and the blade root, the root spacer including a base segment,
a side segment and a groove, wherein

the base segment radially engages the rotor disk;
the side segment is radially separated from the rotor disk defining a gap; and
the groove extends radially into the root spacer at an intersection between the base segment and the side segment.

US Pat. No. 9,404,369

AIRFOIL HAVING MINIMUM DISTANCE RIBS

United Technologies Corpo...

1. An airfoil comprising:
an airfoil body defining a longitudinal axis, the airfoil body including a leading edge and a trailing edge and a first side
wall and a second side wall that is spaced apart from the first side wall to define a camber line there between, the first
side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining a cavity
in the airfoil body; and

four ribs each extending longitudinally in the cavity and being laterally spaced apart from each other relative to the longitudinal
axis,

in at least one plane perpendicular to the longitudinal axis, each of the four ribs connecting the first side wall and the
second side wall along respective minimum distance directions perpendicular to the camber line, at least two of the respective
minimum distance directions are non-parallel, and each of the four ribs has a homogenous microstructure with regard to microstructural
discontinuities, wherein the cavity has a longitudinal span from a base of the airfoil body to a tip end of the airfoil body,
with the base being at 0% of the span and a tip end being at 100% of the span, the at least one plane including a first plane
located at 0%-33% of the span and a second plane located at greater than 33% of the span; and

another plane at greater than 66 percent span wherein the respective minimum distance directions are parallel.

US Pat. No. 9,359,669

METHOD FOR IMPROVED CATHODIC ARC COATING PROCESS

United Technologies Corpo...

1. A cathodic arc cathode formed by melting and casting alloys consisting of a first base alloy and second grain boundary
strengthening alloy addition to the first base alloy;
wherein the first base alloy is selected from the group consisting of NiCrAlY, CoCrAlY, FeCrAlY, NiCoCrAlY, FeCoCrAlY, and
mixtures thereof or NiCrAlYPt, CoCrAlYPt, FeCrAlYPt, NiCoCrAlYPt, FeCoCrAlYPt, and mixtures thereof; and

wherein the second grain boundary strengthening alloy additions to the first base alloy are selected from the group consisting
of about 0.04 to about 0.12 wt. % Zr, about 0.01 to about 0.1 wt. % B, about 10 to about 200 ppm Mgm about 10 to about 200
ppm Ca, about 2 to about 50 ppm Ce and about 5 to about 50 ppm La.

US Pat. No. 9,322,280

METHOD OF MEASURING TURBINE BLADE TIP EROSION

United Technologies Corpo...

1. A method of designing a turbine blade, the method comprising the steps of:
forming at least two notches on a tip of a turbine blade having a pressure side and a suction side, wherein each of the at
least two notches have a known radius, at least one of the at least two notches is located on one of the pressure side and
the suction side, and each of the at least two notches have a different radii;

operating a gas turbine engine including the turbine blade to expand a radial length of the turbine blade such that the tip
of the turbine blade engages a casing;

rubbing the tip of the turbine blade against the casing to wear away a portion of the tip and at least a portion of at least
one of the two notches;

viewing the tip of the turbine blade after the step of operating of the gas turbine engine;
determining an appearance of the at least two notches and the tip; and
determining a manufacturing length of the turbine blade based on the step of determining the appearance the at least two notches.

US Pat. No. 9,193,111

SUPER POLISH MASKING OF INTEGRALLY BLADED ROTOR

United Technologies Corpo...

1. A method of polishing an integrally bladed rotor, the method comprising the steps of:
positioning a mask on an integrally bladed rotor such that a portion of the integrally bladed rotor is unmasked to define
an exposed portion, wherein the step of positioning the mask includes positioning a first projection of a first portion of
the mask in an opening of the integrally bladed rotor; and

polishing the exposed portion of the integrally bladed rotor.

US Pat. No. 9,322,283

AIRFOIL WITH GALVANIC CORROSION PREVENTIVE SHIM

United Technologies Corpo...

1. An airfoil comprising:
an airfoil body made of a first material with a leading edge, trailing edge, pressure side and suction side;
a sheath with first and second flanks made of a second material;
a first shim disposed between a portion of an end of the first flank and the airfoil body and extending beyond the end of
the first flank on the pressure side;

a first adhesive layer disposed between the first shim and the airfoil and connecting the first shim to the airfoil;
a second shim disposed between a portion of an end of the second flank and the airfoil body and extending beyond the end of
the second flank on the suction side; and

a second adhesive layer disposed between the second shim and the airfoil and connecting the second shim to the airfoil.

US Pat. No. 9,249,676

TURBINE ROTOR COVER PLATE LOCK

United Technologies Corpo...

1. A rotor assembly for a gas turbine engine comprising:
a rotor configured for rotation about an engine axis, the rotor including an aft surface including a rotor slot;
a cover plate attached to the aft surface of the rotor, the cover plate including a tab received within the rotor slot and
a cover plate slot aligned with the rotor slot; and

a lock assembly disposed within the rotor slot for holding a position of the cover plate relative to the rotor, the lock assembly
including a key portion conforming to the rotor slot, a lock portion engageable with a surface of the rotor slot and a threaded
member.

US Pat. No. 9,243,500

TURBINE BLADE PLATFORM WITH U-CHANNEL COOLING HOLES

UNITED TECHNOLOGIES CORPO...

1. A turbine blade for a gas turbine engine comprising:
an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil
surface extending in a radial direction, the trailing edge arranged on an aft side of the turbine blade;

a root supporting a platform from which the airfoil extends, and a cooling passage extending within the root in the radial
direction to the airfoil; and

a lower wing arranged beneath the platform on the aft side and extending in an axial direction to provide a U-shaped channel
with the platform that extends in a circumferential direction, and an impingement hole extending from the U-channel to the
cooling passage, wherein the impingement hole is oriented generally in a radial direction, wherein the impingement hole is
configured to direct fluid onto an underside of the platform.

US Pat. No. 9,194,294

GAS TURBINE ENGINE OIL TANK

UNITED TECHNOLOGIES CORPO...

1. A gas turbine engine comprising:
an engine static structure housing a compressor section and a turbine section, and a combustor section arranged axially between
the compressor section and the turbine section;

a core nacelle enclosing the engine static structure to provide a core compartment; and
an oil tank arranged in the core compartment and axially aligned with the compressor section, wherein the oil tank includes
a wall having fins extending through slots in the core nacelle into a bypass flow path.

US Pat. No. 9,273,565

VANE ASSEMBLY FOR A GAS TURBINE ENGINE

United Technologies Corpo...

1. A vane assembly for a gas turbine engine, comprising:
a first platform;
a second platform spaced from said first platform; and said first platform is skewed relative to said second platform; and
a first variable airfoil that extends radially across an annulus between said first platform and said second platform, wherein
one of a radial outer portion and a radial inner portion of said variable airfoil includes a rotational shaft and the other
of said radial outer portion and said radial inner portion includes a ball and socket joint that rotationally connect said
first variable airfoil relative to said first platform and said second platform.

US Pat. No. 9,234,439

GAS TURBINE ENGINE WITH BEARING COMPARTMENT WALL COOLING

United Technologies Corpo...

1. A bearing compartment for a gas turbine engine comprising:
a housing surrounding an engine axis of rotation and having an inner surface and an outer surface spaced radially outward
of the inner surface, the housing defining an open volume for a lubricant, and wherein the housing includes a seat for a bearing
for rotation about the engine axis of rotation, and wherein the housing includes a plurality of cooling protuberances extending
into the open volume, and wherein the inner surface comprises a wetted surface, and wherein the cooling protuberances extend
radially inward from the wetted surface into the lubricant with each cooling protuberance being spaced apart from an adjacent
cooling protuberance by a gap; and

wherein the housing extends from a fore end to an aft end, and wherein the aft end includes an attachment flange configured
for attachment to a non-rotating engine structure, and wherein the inner surface of the housing includes an axial portion,
and wherein the inner surface tapers inwardly in an aft direction from an aft end of the axial portion to form an inward inclined
portion, and wherein the protuberances are formed on at least the axial portion.

US Pat. No. 9,234,522

HYBRID BEARING TURBOMACHINE

United Technologies Corpo...

1. A turbomachine comprising:
a housing;
a rotatable shaft, wherein at least a portion of the rotatable shaft is located in the housing;
a magnetic thurst bearing that axially positions the rotatable shaft;
a radial bearing that centers the rotatable shaft; and
a flexure including a first portion secured to the housing and a second portion axially moveable relative to the first portion,
wherein the second portion contacts the radial bearing, and the second portion moves axially to eliminate thrust loads on
the radial bearing and to allow the magnetic thrust bearing to carry axial loads, wherein the flexure is planar.

US Pat. No. 9,206,499

MINIMIZING BLOCKAGE OF HOLES IN TURBINE ENGINE COMPONENTS

United Technologies Corpo...

1. A method for coating an airfoil, said method comprising:
providing an airfoil, said airfoil having a hole therein,
inserting a plug in said hole, wherein said plug is an omega-shaped plug and said insertion step includes extending the omega-shaped
plug in said hole such that a bulbous top of said plug extends above a depth of a ceramic coating to be placed on said airfoil,

coating said airfoil by a non-line of sight physical vapor deposition, and
removing said plug.

US Pat. No. 9,169,781

TURBINE ENGINE GEARBOX

United Technologies Corpo...

1. A gas turbine engine comprising:
a fan;
a fan drive turbine rotor to drive the fan through a gear reduction; and
the gear reduction including at least two double helical gears in meshed engagement, each of the at least two double helical
gears disposed to rotate about respective axes, and each of the at least two double helical gears having a first plurality
of gear teeth axially spaced from a second plurality of gear teeth by a spacer, wherein each of the first plurality of gear
teeth has a first end facing the spacer and each of the second plurality of gear teeth has a first end facing the spacer,
with each first end of the first plurality of gear teeth being circumferentially offset from each first end of the second
plurality of gear teeth.

US Pat. No. 9,133,542

COATING METHODS AND APPARATUS

United Technologies Corpo...

1. A coating apparatus for coating articles, the coating apparatus comprising:
a coating chamber for coating the articles and having at least one electron beam gun and at least one crucible;
at least one preheat chamber coupled to the coating chamber and comprising:
at least one thermal bed;
at least one electron beam gun positioned to direct an electron beam to the at least one thermal bed; and
at least one thermal hood;
a gas source connected to the preheat chamber;
at least one loading station having:
a proximal end connectable to at least one of the preheat chambers when in an installed position at a distal end of said preheat
chamber;

a carrier for carrying the articles;
a drive system positioned to move the carrier between:
a loading/unloading position of the carrier in the loading station;
a preheat position of the carrier in the preheat chamber to which the loading station is connected; and
a deposition position of the carrier in the coating chamber.

US Pat. No. 9,347,374

GAS TURBINE ENGINE BUFFER COOLING SYSTEM

UNITED TECHNOLOGIES CORPO...

1. A gas turbine engine, comprising:
a heat exchanger that exchanges heat with a bleed airflow to provide a conditioned airflow;
a mid-turbine frame in fluid communication with said heat exchanger;
a passageway that extends through at least a portion of said mid-turbine frame, wherein said conditioned airflow is communicated
through said passageway;

a first nozzle assembly in fluid communication with said passageway to receive said conditioned airflow to condition gas turbine
engine hardware

a bearing compartment positioned radially inwardly from said mid-turbine frame, wherein said bearing compartment is positioned
between said passageway and said first nozzle assembly; and

said conditioned airflow is communicated through said bearing compartment prior to reaching said first nozzle assembly.

US Pat. No. 9,255,491

SURFACE AREA AUGMENTATION OF HOT-SECTION TURBOMACHINE COMPONENT

United Technologies Corpo...

1. A turbomachine hot-section component protrusion, comprising:
a protrusion that extends away from a base surface of the hot-section component along a longitudinal axis, wherein a radial
cross-section of the protrusion has a profile that is non-circular, wherein the protrusion includes at least one planar surface
facing axially away from the base surface and at least three distinct planar surfaces facing away from the axis, the protrusion
including radii that transition the at least one planar surface facing axially away from the base surface into the at least
three distinct planar surfaces facing away from the axis.

US Pat. No. 9,234,481

SHARED FLOW THERMAL MANAGEMENT SYSTEM

United Technologies Corpo...

16. A nacelle assembly for a gas turbine engine comprising:
a core nacelle defined about an axis;
a fan nacelle mounted at least partially around said core nacelle, a bypass flow communicated between said core nacelle and
said fan nacelle;

a multiple of heat exchangers mounted within a bifurcation area in communication with said bypass flow, at least two of said
multiple of heat exchangers arranged in an at least partial-series relationship; and

a vane structure which splits said bypass flow into a modulated heat exchanger flow in communication with at least one of
said multiple of heat exchangers, an unmodulated heat exchanger flow in communication with at least one of said multiple of
heat exchangers and a shared heat exchanger flow in communication with said at least two of said multiple of heat exchangers
arranged in said at least partial-series relationship.

US Pat. No. 9,174,292

ELECTRO CHEMICAL GRINDING (ECG) QUILL AND METHOD TO MANUFACTURE A ROTOR BLADE RETENTION SLOT

UNITED TECHNOLOGIES CORPO...

1. An Electro Chemical Grinding (ECG) quill comprising:
a shaft defined along an axis of rotation; and
a tool mounted to said shaft, said tool manufactured of a porous tool material having a multitude of pores, disposed throughout
the porous tool material, which extend from said shaft to an outer surface, said tool symmetrical defined about said axis
of rotation.

US Pat. No. 9,297,720

GAS TURBINE ENGINE VANE EMBEDDED BEAM INTERRUPT OPTICAL TIP-TIMING PROBE SYSTEM

United Technologies Corpo...

1. A method of embedding a probe in an airflow passage within a gas turbine engine, the method comprising:
housing a first optical fiber within a support, the support in view of an airflow passage;
housing a second optical fiber within a second support opposite the first optical fiber to define a beam across the airflow
passage; and

locating the support within an airfoil;
wherein the gas turbine engine comprises a rotor blade within the airflow passage, and the rotor blade is operable to disrupt
the beam across the airflow passage.

US Pat. No. 9,290,261

METHOD AND ASSEMBLY FOR ATTACHING COMPONENTS

United Technologies Corpo...

1. An adjustable linking member of a mounting assembly, comprising:
a first attachment portion configured to connect a linking member to a first component;
a second attachment portion configured to connect the linking member to a second component;
a variable portion coupling the first attachment portion and the second attachment portion that varies a distance between
the first attachment portion and the second attachment portion in a first direction when heated, and varies the distance between
the first attachment portion and the second attachment portion in a second direction when cooled, the first direction opposite
the second direction; and

a valve configured to selectively permit communication of a fluid to a position near the variable portion to vary the distance,
wherein the valve selectively permits communication of a fluid at a first temperature to the position to vary the distance
in the first direction, and further selectively permits communication of a fluid at a second temperature to the position to
vary the distance in a second direction, the first temperature being greater than the second temperature.

US Pat. No. 9,194,255

OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM

United Technologies Corpo...

1. A turbine engine comprising:
compressor and turbine sections; and
an epicyclic gear train including:
a carrier;
a sun gear and intermediate gears arranged about and intermeshing with the sun gear, the intermediate gears supported by the
carrier; and

a baffle secured to the carrier by an axially oriented fastening member, the baffle including a lubrication passage near at
least one of the sun gear and intermediate gears for directing a lubricant on the at least one of the sun gear and intermediate
gears.

US Pat. No. 9,120,705

REFRACTORYCERAMIC COMPOSITES AND METHODS OF MAKING

United Technologies Corpo...

1. A refractory ceramic composite, comprising a solid monolithic fiber core formed of silicon carbide-containing ceramic material
and a solid ceramic coating continuously disposed directly on said solid monolithic fiber core, said solid ceramic coating
includes a carbide of molybdenum, tungsten boride, or combinations thereof.

US Pat. No. 9,297,261

AIRFOIL WITH IMPROVED INTERNAL COOLING CHANNEL PEDESTALS

United Technologies Corpo...

1. An airfoil for a turbine engine, the airfoil comprising:
a first side wall;
a second side wall spaced apart from the first side wall;
an internal cooling channel formed between the first side wall and the second side wall, the internal cooling channel comprising:
at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to
the second side wall;

a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal
end; and

a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal
end;

wherein at least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery
of the corresponding pedestal end, further wherein the profile is a simple curve described at any point around the periphery
of the corresponding pedestal end by a radius of curvature at a point; the profile at a first point includes a first local
maximum value of the radius of curvature; the first point being a point around the periphery nearest a leading edge of the
airfoil;

a trailing edge;
a pressure side wall connecting the leading edge and the trailing edge; and
a suction side wall spaced apart from the pressure side wall, the suction side wall connecting the leading edge and the trailing
edge; wherein the pressure side wall is the first side wall and the suction side wall is the second side wall.

US Pat. No. 9,452,474

METHOD FOR FORMING A DIRECTIONALLY SOLIDIFIED REPLACEMENT BODY FOR A COMPONENT USING ADDITIVE MANUFACTURING

United Technologies Corpo...

11. A method of manufacturing a replacement body for a component, comprising:
additively manufacturing a replacement body from a metal material;
forming a crucible around the replacement body;
melting and solidifying the replacement body within the crucible to form a directionally solidified microstructure within
the replacement body; and

removing the crucible from the directionally solidified replacement body.

US Pat. No. 9,366,191

FLEXIBLE SHIELD FOR FLUID CONNECTORS

UNITED TECHNOLOGIES CORPO...

1. A flexible shield for fluid connectors of a gas turbine engine, the fluid connector communicating fluid therethrough and
connecting first and second fluid tubes, the flexible shield comprising:
a flexible sleeve surrounding the fluid connector and having a first and second end, the first and second end each being tubular,
the flexible sleeve being a fabric sleeve that is folded into a double-layered structure; and a coupling securing the first
and second end of the flexible sleeve to at least one of the fluid tubes.

US Pat. No. 9,364,897

METHOD AND APPARATUS FOR RECONDITIONING OXIDIZED POWDER

United Technologies Corpo...

1. A metal powder reconditioning apparatus comprising:
an additive manufacturing device configured and operable to produce a metal object from a pulverant material, wherein production
of the metal object from the pulverant material generates contaminated residual powder;

a reducing chamber configured to receive the contaminated residual powder produced by the additive manufacturing device, wherein
the reducing chamber produces reconditioned powder by removing oxygen from the contaminated residual powder;

a container configured to collect the contaminated residual powder from the additive manufacturing device; and
a conveyor configured to receive the contaminated residual powder from the container and transport the contaminated residual
powder to the reducing chamber.

US Pat. No. 9,297,272

GROUNDING FOR FAN BLADES ON AN UNDERBLADE SPACER

United Technologies Corpo...

1. A fan rotor for use in a gas turbine engine comprising:
a rotor body having at least one slot receiving a fan blade;
said fan blade having an outer surface, at least at some areas, formed of a first material and having an airfoil extending
from a dovetail, said dovetail received in said slot;

a spacer positioned radially inwardly of a radially inner face of said dovetail, and biasing said fan blade against said slot,
said spacer including a grounding element; and

the grounding element in contact with a portion of said dovetail formed of a second material that is more electrically conductive
than said first material, and said grounding element being in contact with a rotating element that rotates with said rotor,
said rotating element being formed of a third material, and said first material being less electrically conductive than said
third material, said grounding element and said rotating element together forming a ground path from said portion of said
dovetail into said rotor.

US Pat. No. 9,284,889

FLEXIBLE SEAL SYSTEM FOR A GAS TURBINE ENGINE

United Technologies Corpo...

1. A flexible seal system for a gas turbine engine, comprising:
an annular mounting bracket;
an annular support bracket;
an annular flexible seal extending axially between a first mounting segment and a second mounting segment, wherein the first
mounting segment is connected axially between the mounting bracket and the support bracket, and comprises a plurality of mounting
apertures that extend axially through the first mounting segment; and

a plurality of mounting spacers, each arranged within a respective one of the mounting apertures, and extending axially between
the mounting bracket and the support bracket;

wherein the flexible seal is constructed from an elastomer composite that comprises a plurality of fibers, and wherein a quantity
of the fibers are laid oblique to an axially extending contour line of the flexible seal.

US Pat. No. 9,103,214

CERAMIC MATRIX COMPOSITE VANE STRUCTURE WITH OVERWRAP FOR A GAS TURBINE ENGINE

UNITED TECHNOLOGIES CORPO...

1. A vane structure for a gas turbine engine comprising:
a ring defined about an axis;
an airfoil section with a platform segment abutting said ring, said airfoil section comprising a multiple of CMC plies;
an insert adjacent to said platform segment; and
an overwrap wound around said ring, said insert, and a fillet portion of said multiple of CMC plies of said airfoil section
in a continuous spiral, said overwrap biasing said multiple of CMC plies toward said ring.

US Pat. No. 9,321,116

COLD METAL TRANSFER GAS METAL ARC WELDING APPARATUS AND METHOD OF OPERATION

United Technologies Corpo...

1. A cold metal transfer (CMT) welding apparatus, comprising:
a CMT contact tip having a contact surface that is a substantially copper-free metal that contains essentially no copper;
a weld wire in physical contact with the contact surface; and
a CMT wire feeder constructed and arranged to feed the weld wire through the CMT contact tip with an axially oscillating motion
with respect to a centerline axis of the CMT contact tip.

US Pat. No. 9,170,224

MULTIPLE-EXCITATION MULTIPLE-RECEIVING (MEMR) CAPACITANCE TOMOGRAPHY

The University of Connect...

1. An electrical capacitance tomography (ECT) sensor comprising:
a plurality of electrodes, each configured to operate exclusively as an excitation electrode in a first condition and exclusively
as a receiving electrode in a second condition, wherein a first set of electrodes in said plurality of electrodes includes
more than one electrode and a second set of electrodes in said plurality of electrodes includes more than one electrode, each
electrode in the first set of electrodes being in the first condition simultaneously, and each electrode in the second set
of electrodes being in the second condition simultaneously;

an electrode control module connected to each of the plurality of electrodes and configured to control a condition of each
of the plurality of electrodes; and

a plurality of lock-in amplifiers connected to an output of the electrode control module and connected to a data acquisition
system of a computer.

US Pat. No. 9,097,186

BEVEL GEAR ARRANGEMENT FOR AXIAL ACCESSORY GEARBOX

United Technologies Corpo...

1. An accessory box for a gas turbine engine comprising: an input gear to be driven by an input shaft;
said input gear engaged to drive a first driven gear on one radial side of a drive axis of said input gear;
said first driven gear driving at least a second driven gear on said one radial side of said drive axis, with at least one
accessory driven by one of said first driven gear and said second driven gear;

said second driven gear driving a bevel gear arrangement to drive a third driven gear on an opposed side of said drive axis
of said input gear, and said third driven gear driving at least a second accessory; and

said one accessory and said second accessory to be associated with a gas turbine engine.

US Pat. No. 9,234,463

THERMAL MANAGEMENT SYSTEM FOR A GAS TURBINE ENGINE

United Technologies Corpo...

1. A thermal management system for a gas turbine engine comprising:
means for delivering a first stream of cooling air to at least one forward cavity for controlling disk temperature and shaft
temperature;

means for allowing said first stream of cooling air to exit said at least one forward cavity;
means for delivering a second stream of cooling air to at least one aft cavity for providing disk web cooling; and
means for mixing said first stream of cooling air exiting said at least one forward cavity with an intershaft flow of cooling
air, wherein said at least one forward cavity comprises a plurality of forward cavities formed by a plurality of disks, hubs
and an outer diameter of a shaft and said at least one aft cavity comprises a plurality of aft cavities formed by a plurality
of disks and the outer diameter of said shaft.

US Pat. No. 9,366,144

TRAILING EDGE COOLING

United Technologies Corpo...

1. An airfoil comprising:
a leading edge and a trailing edge;
a suction surface and a pressure surface, the suction surface and the pressure surface both extending axially between the
leading edge and the trailing edge, as well as radially from a root section to a tip section of the airfoil;

a cooling passageway located between the suction surface and the pressure surface; and
a plurality of oblong pedestals connecting the suction surface to the pressure surface, the oblong pedestals having a cut
downstream end perpendicular to a directly adjacent flowpath of the cooling passageway and connecting a downstream end of
the pressure surface and a downstream end of the suction surface, the oblong pedestals terminating at the trailing edge of
the airfoil.

US Pat. No. 9,322,554

TEMPERATURE MIXING ENHANCEMENT WITH LOCALLY CO-SWIRLING QUENCH JET PATTERN FOR GAS TURBINE ENGINE COMBUSTOR

United Technologies Corpo...

1. A combustor for a turbine engine comprising:
a first liner defined about a liner axis with a first row of first combustion air holes circumferentially distributed about
said liner axis, at least some of said first combustion air holes coaxially aligned with a corresponding fuel injector zero
pitch line axis projecting from a centerline of a respective fuel injector of a plurality of fuel injectors;

a second liner defined about said liner axis with a second row of second combustion air holes circumferentially distributed
about said liner axis, each of said second combustion air holes coaxially misaligned relative to each of said fuel injector
zero pitch line axes; and

wherein said first row of first combustion air holes is a plurality of three hole sets in a four hole repeating pattern that
includes a major air hole, a first minor air hole that is smaller than said major air hole and an intermediate air hole that
is smaller than said major air hole and lamer than said first minor air hole.

US Pat. No. 9,334,751

VARIABLE VANE INNER PLATFORM DAMPING

United Technologies Corpo...

1. A variable vane damper, comprising:
a body comprised of a resilient material, the body including a first surface that is bondable to an inner platform of a variable
vane and a second surface that is bondable to an inner diameter trunnion component.

US Pat. No. 9,222,417

GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE

United Technologies Corpo...

1. A gas turbine engine comprising:
a combustor;
a turbine section in fluid communication with the combustor, the turbine section including a fan drive turbine and a second
turbine section, the fan drive turbine including a plurality of turbine rotors;

a fan including a plurality of blades rotatable about an axis and a ratio between a number of fan blades and a number of fan
drive turbine rotors is between about 2.5 and about 8.5; and

a speed change system driven by the fan drive turbine for rotating the fan about the axis;
wherein the fan drive turbine has a first exit area at a first exit point and rotates at a first speed, the second turbine
section has a second exit area at a second exit point and rotates at a second speed, which is faster than the first speed,
wherein a first performance quantity is defined as a product of the first speed squared and the first exit area, a second
performance quantity is defined as a product of the second speed squared and the second exit area, and a performance ratio
of the first performance quantity to the second performance quantity is between about 0.5 and about 1.5.

US Pat. No. 9,127,622

REVERSIBLE FLOW DISCHARGE ORIFICE

UNITED TECHNOLOGIES CORPO...

1. A fluid flow system comprising:
an orifice providing a throat having a throat radius, the orifice including entrance and exit ramps adjoining either side
of the throat, the entrance ramp providing a smooth approach to the orifice throat, and the exit ramp including an exit ramp
surface having a divergent angle of 20-60° and an exit ramp radius adjoining the exit ramp at a location near the throat,
the exit ramp radius less than twice the throat radius;

a shut-off valve having open and closed positions;
a pump fluidly connected to the shut-off valve by a fluid passage, wherein a tube is arranged in the fluid passage, the tube
includes the orifice; and

wherein the pump is configured to convey a fluid through the orifice in a first direction with the shut-off valve in the open
position, the fluid flows from the entrance ramp to the exit ramp in the first direction, and the pump is configured to reverse
the flow of fluid through the orifice to a second direction opposite the first direction with the shut-off valve in the closed
position.

US Pat. No. 9,115,650

RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME

United Technologies Corpo...

1. A turbine engine comprising:
a fan section including a plurality of fan blades;
a turbine section;
an epicyclic gear train coupled between the turbine section and the fan section for providing a speed reduction between turbine
section and the fan section, the epicyclic gear train including a plurality of intermediate gears, a carrier supporting the
plurality of intermediate gears, a sun gear that meshes with the plurality of intermediate gears and a ring gear surrounding
and meshing with the plurality of intermediate gears the ring gear including first and second portions that each have an inner
periphery with teeth, wherein the first and second portions of the ring gear have an outer circumferential surface opposite
the teeth that provides a first thickness, a second thickness greater than the first thickness and axially inward from the
first thickness, and a flange extending radially away from said axis; and

an oil collection feature having an angled portion that is angled relative to the axis, and a radially aligned portion connected
to the flange.

US Pat. No. 9,080,449

GAS TURBINE ENGINE SEAL ASSEMBLY HAVING FLOW-THROUGH TUBE

United Technologies Corpo...

1. A seal assembly for a gas turbine engine, comprising:
an annular body that includes a first flange and a second flange spaced from said first flange, said first flange and said
second flange both including an upstream face and a downstream face;

a flow-through tube extending through said upstream face and said downstream face of each of said first flange and said second
flange of said annular body and including an upstream orifice, a downstream orifice and a tube body that extends between said
upstream orifice and said downstream orifice, said tube body including an axial portion and a tangential portion, wherein
said axial portion and said tangential portion together communicate a conditioning airflow in an upstream direction from said
downstream orifice toward said upstream orifice of said flow-through tube.

US Pat. No. 9,382,875

SPHERICAL BUTTON WASHER FOR EXHAUST DUCT LINER HANGER

United Technologies Corpo...

1. A hanger for use in a gas turbine engine exhaust system, the hanger comprising:
a bracket for connection to an exhaust duct liner of the gas turbine exhaust system;
a washer connected to the bracket at a slip joint;
a rod connected to the washer at a ball joint; and
a cap for connecting to an exhaust duct of the gas turbine exhaust system, the cap connected to the rod, wherein the slip
joint and the ball joint restrain a first end of the rod in a generally radially direction and permit movement in all other
rotational and translational directions, and wherein a second end of the rod is fixed such that the second end of the rod
is translationally restrained with respect to the cap and translations of the first end of the rod relative to the second
end of the rod are rotationally restrained at the second end.

US Pat. No. 9,327,368

FULL RING INNER AIR-SEAL WITH LOCKING NUT

United Technologies Corpo...

17. A method of assembling a vane assembly comprising:
defining a plurality of vanes circumferentially about an axis that extend from an inner platform;
abutting a front rim of the inner platform against a forward lip of an air seal;
installing a ring nut on an aft end of the air seal;
providing a biasing force against the ring nut to prevent the ring nut from rotating relative to the air seal; and
overcoming the biasing force to allow the ring nut to rotate to a lock position with the biasing force subsequently returning
the ring nut to a non-rotatable condition.

US Pat. No. 9,239,030

NACELLE ELECTRICAL LOCKING SYSTEM FOR LEADING EDGE OF OPENABLE PANEL

United Technologies Corpo...

1. A nacelle structure for a gas turbine engine comprising:
an outer nacelle surrounding a fan section and defining an outer boundary of a bypass flow passage;
an inner nacelle surrounding a core engine section and defining an inner boundary of the bypass flow passage;
a panel of the inner nacelle moveable between an open position providing access to the core engine section and a closed position;
a lock supported within the inner nacelle proximate the panel, the lock including an electric actuator for moving a locking
pin between a locked position preventing opening of the panel and an unlocked position;

a blocker mounted to a fixed structure of the core engine section blocking movement of the locking pin when the locking pin
is in the locked position, wherein the locking pin is spaced radially apart from the blocker when in the locked position;
and

a series of latches providing a latching function for holding the panel in the closed position;
wherein operation of the lock is independent of the latching function.

US Pat. No. 9,115,897

GAS TURBINE ENGINE SYSTEMS AND METHODS INVOLVING ENHANCED FUEL DISPERSION

United Technologies Corpo...

1. A gas turbine engine system comprising:
a vane positioned relative to a longitudinal axis of the engine;
a fuel conduit operative to receive a flow of fuel and disperse the fuel though a fuel nozzle;
a mounting component which positions the fuel conduit with respect to the vane, the mounting component defines an aperture
through which the fuel conduit is mounted, the aperture of a shape different than the fuel conduit to define an airflow gap
which corresponds to a direction at which the fuel is dispersed; and

an igniter which extends through the mounting component.

US Pat. No. 9,097,131

AIRFOIL AND DISK INTERFACE SYSTEM FOR GAS TURBINE ENGINES

United Technologies Corpo...

1. A gas turbine engine system comprising:
a disk having a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending
radially outward from the second rail;

an airfoil engaged with the retention slot, the airfoil having a platform with an upstream angled portion, a downstream angled
portion, and a notch defined in the platform, wherein the ridge of the disk extends at least partially into the notch of the
platform;

a ladder seal system position at least partially between the platform of the airfoil and the disk, wherein the ladder seal
system comprises a plurality of arcuate ladder seal segments; and

the ladder seal is arranged to conform to the platform angled portions, in an uninstalled state.

US Pat. No. 9,452,470

SYSTEM AND METHOD FOR HIGH TEMPERATURE DIE CASTING TOOLING

United Technologies Corpo...

1. A method for die casting a metal having a melting temperature of at least 1500° F. (815° C.), the method comprising the
steps of:
injecting a molten volume of the metal into an interior volume of a casting die, the casting die comprising a main cavity
corresponding to an as-cast structure, a first reservoir having dimensions with an aspect ratio (height to cross-sectional
area) between 0.5 and 2.0, and a first runner arrangement having at least one runner configured into one or more wedges serially
connecting the first reservoir and the main cavity to fluidly communicate molten metal between the first reservoir and the
main cavity, the molten volume sufficient for filling the main cavity, the first reservoir and at least a portion of the first
runner arrangement;

venting vapor through a vent in serial fluid communication with the first reservoir, the vent having at least one passage
for evacuating vapor from the interior volume;

after the injecting step and the venting step, sealing the casting die;
equiaxially solidifying the injected molten volume of metal, solidification proceeding generally from a first portion of the
main cavity distal to the first reservoir toward a second portion of the main cavity proximal to the first reservoir; and

during the equiaxial solidifying step, backfilling the main cavity with at least a portion of the injected molten volume via
the first runner arrangement to substantially maintain a continuous solidification front within the main cavity.

US Pat. No. 9,404,384

GAS TURBINE ENGINE SYNCHRONIZING RING WITH MULTI-AXIS JOINT

United Technologies Corpo...

1. A gas turbine engine comprising:
an engine case;
a compressor and/or turbine section having at least a first stage of variable vanes circumferentially spaced radially inward
of the engine case;

a synchronizing ring disposed about the engine case wherein the synchronizing ring has an I-beam cross-sectional shape with
channels in opposing surfaces of the synchronizing ring wherein one channel is on a surface facing radially inward;

a plurality of vane arms connected to the variable vanes; and
a plurality of multi-axis joints connecting the synchronizing ring to the vane arms, each multi-axis joint providing each
vane arm with movement about a first pivot axis and a second pivot axis, wherein the plurality of multi-axis joints interface
with the channels in the synchronizing ring, wherein the multi-axis joints each have a first trunnion that is held within
the synchronizing ring by a cover plate.

US Pat. No. 9,315,905

COATED ARTICLE AND COATING PROCESS THEREFOR

United Technologies Corpo...

1. A coating process comprising:
preheating a workpiece having an aluminum-containing layer through a temperature range in a reducing atmosphere having hydrogen
to thereby limit formation of thermally grown oxides on the surfaces of the workpiece;

introducing a source of oxygen to establish an oxidizing atmosphere at a temperature above the temperature range to form a
desired type of thermally grown oxide on the surfaces of the workpiece; and

depositing a coating on the desired type of thermally grown oxide wherein the preheating is conducted at approximately ambient
pressure.

US Pat. No. 9,212,556

MULTIFUNCTION POSITIONING LOCK WASHER

United Technologies Corpo...

1. A gas turbine engine section comprising:
a rotatable shaft;
axially adjacent stationary and rotating components located on the rotatable shaft and separated by an axial separation distance;
a nut configured to thread onto the rotatable shaft to hold one of the axially adjacent stationary and rotating components
in compression;

a multifunction positioning lock washer with antirotation geometry configured to prevent the nut from tightening or loosening,
wherein an axial length of the multifunction positioning lock washer is adjusted by removing material based on measurement
of the axial separation distance to define the axial separation distance by spacing the stationary component relative to the
rotating component.

US Pat. No. 9,188,009

BORE CAVITY THERMAL CONDITIONING SYSTEM

United Technologies Corpo...

1. A gas turbine engine comprising:
a rotor comprising at least one rotor bore cavity; and
a heat exchanger fluidically connected to a conditioning air source and to the rotor bore cavity for flowing air from the
conditioning air source to the rotor bore cavity, wherein the heat exchanger is also fluidically connected to a hot fluid
source and a cool fluid source for selectively heating and cooling conditioning air flowing to the rotor bore cavity.

US Pat. No. 9,249,685

FAN DRIVE GEAR SYSTEM ASSEMBLY GUIDE

United Technologies Corpo...

1. A gas turbine engine comprising:
a fan, a turbine section including a turbine rotor to drive said fan through a gear reduction module;
an input shaft downstream of said turbine rotor including a flexible mount driving said gear reduction module, and said input
shaft being mounted within a bearing module, and said gear reduction module having static structure mounted to an engine housing
through a flexible mount; and

an oil supply system to supply oil into said gear reduction module, and an oil tube to supply oil from said gear reduction
module to said bearing module, said oil tube being received within an opening in said static structure, and in an opening
in a housing for said bearing module, and said oil tube extending through an assembly guide having a guide opening which is
spaced away from an outer periphery of said oil tube, and said guide opening is intermediate said opening in said static structure,
and said opening in said bearing housing.

US Pat. No. 9,222,364

PLATFORM COOLING CIRCUIT FOR A GAS TURBINE ENGINE COMPONENT

United Technologies Corpo...

1. A gas turbine engine, comprising:
a compressor section;
a combustor section in fluid communication with said compressor section;
a turbine section in fluid communication with said combustor section; and
wherein one of said compressor section and said turbine section includes at least one component having a platform that includes
a platform cooling circuit, wherein said platform cooling circuit includes:

a first core cavity;
a second core cavity adjacent to said first core cavity;
a cavity in fluid communication with said first core cavity and said second core cavity; and
said first core cavity configured to communicate a cooling airflow into a first inlet of a first portion of said cavity and
said second core cavity configured to feed said cooling airflow into a second inlet of a second portion of said cavity.

US Pat. No. 9,217,590

EJECTOR CYCLE

United Technologies Corpo...

1. A system (200; 300; 400; 500; 600) comprising:
a compressor (22; 220, 221);

a heat rejection heat exchanger (30) coupled to the compressor to receive refrigerant compressed by the compressor;

an ejector (38) having:

a primary inlet (40);

a secondary inlet (42); and

an outlet (44);

a heat absorption heat exchanger (64);

a separator (48) having:

an inlet (50) coupled to the outlet of the ejector to receive refrigerant from the ejector;

a gas outlet (54); and

a liquid outlet (52); and

one or more valves (244, 246, 248, 250) and a controller (140) configured to operate the one or more valves to switch the system between:

a first mode wherein:
refrigerant passes sequentially from the heat rejection heat exchanger, through the ejector primary inlet, out the ejector
outlet, to the separator;

a first flow from the separator gas outlet passes through the compressor to the heat rejection heat exchanger; and
a second flow from the separator liquid outlet passes through the heat absorption heat exchanger and through the ejector secondary
inlet; and

a second mode wherein:
flow through the ejector secondary inlet is blocked:
refrigerant passes from the heat rejection heat exchanger to the separator;
a first flow from the separator gas outlet passes to the compressor; and
a second flow from the separator liquid outlet passes through the heat absorption heat exchanger to the compressor bypassing
the ejector.

US Pat. No. 9,169,731

AIRFOIL COVER SYSTEM

United Technologies Corpo...

1. An airfoil for a gas turbine engine comprising:
a body having a first surface extending from a first edge to a second edge;
a cavity disposed in the body;
a first cover at least partially disposed within the cavity, the first cover comprising a first portion cooperating with a
corresponding second portion;

a second cover covering said first cover and forming at least a portion of the first surface with said body, wherein the first
cover is disposed between the body and the second cover, wherein the first cover and the second cover have a different coefficient
of thermal expansion than the body; and

wherein a flexible material is disposed in a gap between the first portion and the second portion, the gap defined between
corresponding edges of the first portion and the second portion.

US Pat. No. 9,169,739

HYBRID BLADE OUTER AIR SEAL FOR GAS TURBINE ENGINE

UNITED TECHNOLOGIES CORPO...

1. A Blade Outer Air Seal (BOAS) comprising:
a body including a face opposite a forward interface and an aft interface, said face including a first cavity and a second
cavity axially spaced from said first cavity; and

a first non-metallic insert provided within said first cavity and a second non-metallic insert provided within said second
cavity, wherein said first and second non-metallic inserts are flush with said face.

US Pat. No. 9,140,139

STRUCTURAL JOINT FOR CONNECTING A FIRST COMPONENT TO A SEGMENTED SECOND COMPONENT

United Technologies Corpo...

1. A structural joint, comprising:
a first flange extending out from a first component to a distal first flange end;
a second flange extending out from a segmented second component to a distal second flange end, and comprising a first lateral
flange segment extending laterally to a first flange sidewall and a second lateral flange segment extending laterally to a
second flange sidewall that is engaged with the first flange sidewall; and

a fastener comprising a head and a shaft, wherein the head is encased in the second flange and extends laterally into the
first flange sidewall and the second flange sidewall, and the shaft extends longitudinally out from the second flange and
through the first flange.

US Pat. No. 9,435,259

GAS TURBINE ENGINE COOLING SYSTEM

United Technologies Corpo...

15. A method of conditioning a portion of a gas turbine engine, comprising:
removing heat from a bleed airflow to render a conditioned airflow;
communicating the conditioned airflow through a plenum disposed inside a diffuser case, the diffuser case including an outer
circumferential wall and an inner circumferential wall that is circumscribed by the outer circumferential wall, the plenum
extends radially from the outer circumferential wall to the inner circumferential wall, and said plenum extends along an entire
axial length of said diffuser case; and

feeding the conditioned airflow through a nozzle assembly to a downstream location of the gas turbine engine.

US Pat. No. 9,422,066

GROUNDING SLEEVE

United Technologies Corpo...

1. An assembly comprising:
a first metal component;
a second metal component;
a composite component disposed between the first metal component and the second metal component, the composite component comprising:
an electrically conductive element disposed within the composite component;
a hole extending through the first metal component and the composite component, and into the second metal component;
a fastener disposed in the hole and connecting the first metal component, the second metal component and the composite component
together; and

a sleeve disposed in the hole and around the fastener, wherein the fastener compresses the sleeve inside the hole such that
the sleeve deflects and contacts the electrically conductive element while the sleeve maintains contact with the fastener,
thereby forming a grounding path with the first metal component, the composite component, and the second metal component,
wherein the sleeve comprises:

a first annular ring;
a second annular ring disposed opposite the first annular ring and spaced from the first annular ring; and
a thin elongated element extending from the first annular ring to the second annular ring.

US Pat. No. 9,410,427

COMPRESSOR POWER AND TORQUE TRANSMITTING HUB

United Technologies Corpo...

1. A compressor hub comprising:
a sleeve portion that is cylindrical about a sleeve axis; wherein the sleeve portion includes an inner sleeve surface opposing
an outer sleeve surface, the inner sleeve surface having an inner spline and the outer sleeve surface having an outer spline

a frustoconical cone portion attached to the sleeve portion that diverges forward and radially outward, the cone portion comprising:
an inner cone portion adjacent to the sleeve portion, the inner cone portion having a frustoconical shape including a forward
inner cone surface opposing an aftward inner cone surface that are bisected by an inner generatrix that is equidistant from
the forward inner cone surface and the aftward inner cone surface; and

an outer cone portion adjacent to the inner cone portion, the outer cone portion having a frustoconical shape including a
forward outer cone surface opposing an aftward outer cone surface that are bisected by an outer generatrix that is equidistant
from the forward outer cone surface and the aftward outer cone surface, wherein the inner generatrix and the outer generatrix
are colinear; and

a mounting flange portion attached to the outer cone for attaching a rotor disk to the compressor hub.

US Pat. No. 9,145,771

ROTOR ASSEMBLY DISK SPACER FOR A GAS TURBINE ENGINE

United Technologies Corpo...

1. A disk spacer for a gas turbine engine, comprising:
a rim;
a bore;
a web that extends between said rim and said bore,
a load path spacer that extends from said web and is spaced from each of said rim and said bore; and
at least one fin that extends along a portion of said web, wherein said at least one fin is configured to induce radial inflow
of a bleed airflow communicated across said at least one fin, and wherein said load path spacer axially extends further from
said web than said at least one fin.

US Pat. No. 9,121,280

TIE SHAFT ARRANGEMENT FOR TURBOMACHINE

UNITED TECHNOLOGIES CORPO...

1. A turbomachine comprising:
a tie shaft extending along an axis;
multiple rotors mounted on the tie shaft;
first and second clamping members secured to the tie shaft and exerting a clamping load between the rotors and clamping members
at multiple interfaces, the clamping load at one of the interfaces including a radial clamping load of greater than 5% of
a total design clamping load at the one interface; and

a friction modifier is provided at the interface, wherein the interface includes at least one of a rough surface finish, a
grit blasted surface, a coating, a spray, a plasma, colloidal particles, adhesives, pastes and additives.

US Pat. No. 9,091,176

TURBOMACHINERY COMPONENT COOLING SCHEME

United Technologies Corpo...

1. An airfoil comprising:
a suction surface and a pressure surface both extending axially between a leading edge and a trailing edge region, as well
as radially from a root section of the airfoil to a tip section of the airfoil;

a first protuberance and a second protuberance both extending axially along the pressure surface at the trailing edge region,
the first protuberance and the second protuberance spaced apart by a trough;

a primary cooling outlet located in the trough; and
a first secondary cooling outlet located on the first protuberance and a second secondary cooling outlet located on the second
protuberance, wherein the first secondary cooling outlet and the second secondary cooling outlet are located upstream of the
primary cooling outlet.

US Pat. No. 9,410,905

NON-DESTRUCTIVE INSPECTION OF AN ARTICLE USING CROSS-SECTIONS THROUGH INTERNAL FEATURE

United Technologies Corpo...

1. A method of non-destructively inspecting an article, the method comprising:
scanning an article to produce a computerized three-dimensional representation of an internal feature of the article;
generating a measurement characteristic of the internal feature from a plurality of cross-sections through the computerized
three-dimensional representation of the internal feature, wherein the measurement characteristic is a central axis of the
internal feature; and

using the measurement characteristic to determine whether the internal feature meets a design criterion.

US Pat. No. 9,410,435

GAS TURBINE ENGINE COMPONENT WITH DIFFUSIVE COOLING HOLE

United Technologies Corpo...

1. A component for a gas turbine engine, the component comprising:
a gas path wall having a first surface and a second surface, wherein the second surface is exposed to hot gas flow; and
a cooling hole extending through the gas path wall, the cooling hole comprising:
an inlet formed in the first surface;
an outlet formed in the second surface;
cooling hole surfaces that define the cooling hole between the inlet and the outlet; and
a first longitudinal ridge formed along at least one of the cooling hole surfaces, the longitudinal ridge separating the cooling
hole into first and second lobes;

a second longitudinal ridge formed along at least one of the cooling hole surfaces, the longitudinal ridge separating the
cooling hole into second and third lobes; and

a ridge nexus spaced along the cooling hole between the inlet and the outlet, wherein the first and second longitudinal ridges
meet at the ridge nexus, wherein the second lobe is positioned between the first and third lobes, and wherein the second lobe
truncates at the ridge nexus; and

wherein the cooling hole diverges through the gas path wall, such that cross-sectional area of the cooling hole increases
continuously from the inlet through the cooling hole to the outlet.

US Pat. No. 9,366,586

HIGH TEMPERATURE UNCOOLED OPTICAL PROBE

United Technologies Corpo...

1. An optical probe comprising:
a first end;
a second end;
an outer housing;
an inner housing concentric with the outer housing;
a plurality of flow holes within the inner housing at the first end;
an optics holder having a low coefficient of thermal expansion within the inner housing between the plurality of flow holes
and the second end;

a plurality of high temperature optical lenses inside the optics holder between the plurality of flow holes and the second
end;

a plurality of fiber holders having a low coefficient of thermal expansion inside the optics holder between the plurality
of high temperature optical lenses and the second end;

a plurality of optical fibers extending from inside the plurality of fiber holders towards the second end and coated in gold
or copper to allow the optical fibers to withstand temperatures of up to at least 1120 degrees Fahrenheit; and

a high temperature adhesive capable of withstanding up to 2200 degrees Fahrenheit for securing the plurality of optical fibers,
the plurality of fiber holders, and the plurality of high temperature optical lenses, so that the optical probe can withstand
temperatures of up to 1120 degrees Fahrenheit;

wherein the plurality of flow holes are configured to expel gaseous nitrogen across an outer surface of the high temperature
optical lenses.

US Pat. No. 9,249,668

AIRFOIL WITH BREAK-WAY, FREE-FLOATING DAMPER MEMBER

United Technologies Corpo...

15. A method for processing an airfoil, the method comprising:
depositing multiple layers of a powdered metal onto one another;
joining the layers to one another with reference to data relating to a particular cross-section of an airfoil; and
producing the airfoil with a body including an airfoil body including a leading edge and a trailing edge and a first side
wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining
the leading edge and the trailing edge and at least partially defining a cavity in the airfoil body, and a damper member enclosed
in the cavity, the damper member being connected to the body in a break-away joint, wherein the minimum cross-sectional area
of the break-away joint is less than a critical cross-sectional area needed to support the mass of the damper member during
rotation of the airfoil body.

US Pat. No. 9,243,501

TURBINE AIRFOIL PLATFORM RAIL WITH GUSSET

UNITED TECHNOLOGIES CORPO...

1. A blade for a gas turbine engine comprising:
a shank interconnecting a root and a platform, and an airfoil extending radially from the shank, the shank including a pocket
with the platform overhanging the pocket;

a rail extending axially along a lateral edge of the platform and extending radially inward from the platform in a direction
opposite the airfoil; and

a gusset extending from an underside of the platform facing the pocket and in a circumferential direction between the rail
and the shank, wherein the gusset is interconnected to the rail and the platform underside but the gusset is spaced from a
surface of the pocket.

US Pat. No. 9,221,720

DENSE PROTECTIVE COATINGS, METHODS FOR THEIR PREPARATION AND COATED ARTICLES

UNITED TECHNOLOGIES CORPO...

1. A method for depositing a protective coating on a complex shaped substrate, comprising the steps of:
(1) forming a base coat on a complex shaped substrate comprising a gas turbine engine component by dipping said complex shaped
substrate into a slurry consisting of an aqueous solution, at least one refractory metal addition of at least 25 mol. % of
a first refractory metal oxide selected from the group consisting of hafnium oxide and monoclinic hafnium oxide and up to
about 25 mol. % of at least one second refractory metal oxide, a dispersing agent in an amount no more than 50 percent weight
of the slurry, and at least one transient fluid additive being a source of silica or titania, said transient fluid additive
being present in an amount of about 0.1 percent to 10 percent by weight of said slurry and being used to promote grain growth
and eliminate the formation of pores between grains;

(2) curing said dipped substrate, wherein curing comprises heating said substrate to a temperature of between about 1250°
C. to 1450° C. for about 30 minutes to 500 minutes;

(3) dipping said substrate into a precursor solution to form a top barrier coat thereon; and
(4) heat treating said dipped, cured substrate to form a protective coating.

US Pat. No. 9,194,330

RETROFITABLE AUXILIARY INLET SCOOP

United Technologies Corpo...

1. A nacelle assembly comprising:
a fan nacelle;
a core nacelle spaced radially inwardly of the fan nacelle to define a bypass flowpath; and
a scoop to direct air from the bypass flowpath into an engine core, wherein the scoop is comprised of a first piece extending
outwardly of an outer surface of the core nacelle to define an air inlet and a second piece extending inwardly relative to
the core nacelle to define an air outlet, and wherein the scoop is attached to an inner structure of the core nacelle at a
first attachment interface and the first and second pieces are attached to each other via a second attachment interface, and
wherein the first and second attachment interfaces are located internally of the core nacelle.

US Pat. No. 9,175,570

AIRFOIL INCLUDING MEMBER CONNECTED BY ARTICULATED JOINT

United Technologies Corpo...

1. An airfoil comprising:
a body including a platform, an airfoil extending outwardly from a side of the platform and a root extending outwardly from
another side of the platform, the body having one of a socket or a socket member that are connected together in an articulated
joint; and

a member including the other of the socket member or the socket, the socket member irremovably interlocked with the socket
such that the socket member cannot be removed from the socket non-destructively.

US Pat. No. 9,151,183

RETRACTABLE EXHAUST LINER SEGMENT FOR GAS TURBINE ENGINES

United Technologies Corpo...

1. A retractable exhaust liner segment comprising:
a first retractable exhaust liner segment which defines a first flange;
a second retractable exhaust liner segment which defines a second flange;
a fastener assembly received by said first flange and said second flange configured to mount said first retractable exhaust
liner segment and said second retractable exhaust liner segment;

wherein a forward end of said retractable exhaust liner segment overlaps an aft end of an engine structure and an aft end
of said retractable exhaust liner segment overlaps a forward end of an exhaust liner in an assembled position; and

wherein a gap exists between said retractable exhaust liner segment and one of the engine structure and the exhaust liner
as said retractable exhaust liner segment is moved along an axis in one direction to a disassembled position and the gap closes
as said retractable exhaust liner segment is moved along the axis in other direction to the assembled position.

US Pat. No. 9,054,610

GENERATOR ARCHITECTURE WITH MAIN FIELD ROTATING POWER CONVERTER

United Technologies Corpo...

1. A generator comprising:
a stationary portion that includes a main armature winding;
a rotating portion that includes a main field winding and a main field rotating power converter that selectively controls
current supplied to the main field winding;

a stationary communication module located on the stationary portion;
a rotating communication module located on the rotating portion that is coupled to receive input from the stationary communication
module, wherein the rotating communication module communicates instructions received from the stationary communication module
to the main field rotating power converter to selectively apply the DC voltage provided by the DC link bus to the main field
winding; and

wherein the stationary communication module includes a first primary winding and the rotating communication module includes
a first secondary winding inductively coupled to the first primary winding and a second secondary winding inductively coupled
to the first primary winding.

US Pat. No. 9,452,468

DEEP ROLLING TOOL WITH FORCE ADJUSTMENT

UNITED TECHNOLOGIES CORPO...

1. A deep rolling tool for applying compressive stress with rolling elements, the deep rolling tool comprising:
a flexible fork having a base section and a plurality of fork arms extending outwardly from the base section without a pivot,
each of the plurality of fork arms having a distal end with respect to the base section, wherein the distal end comprises
an aperture; and

a plurality of rolling elements, wherein each of the plurality of rolling elements is rotatably mounted to one of the plurality
of fork arms via eccentric roller bushings, and wherein each of the plurality of rolling elements are located within the aperture
of the respective distal end of each of the plurality of fork arms, and wherein at least two of the plurality of rolling elements
are configured to define an opening therebetween, the opening being located between at least two of the plurality of fork
arms, and wherein the plurality of rolling elements apply a compressive stress to a metal article located in the opening.

US Pat. No. 9,403,102

HEAT EXCHANGE SYSTEM CONFIGURED WITH A MEMBRANE CONTACTOR

United Technologies Corpo...

1. A heat exchange system, comprising:
a first heat exchange circuit that circulates a first working fluid sequentially through a first heat exchanger, a second
heat exchanger and a membrane contactor; and

a second heat exchange circuit that directs a second working fluid sequentially through the first heat exchanger and the membrane
contactor, the second working fluid comprising solute and solvent;

wherein the first heat exchanger and the membrane contactor transfer heat energy from the second working fluid to the first
working fluid, and the second heat exchanger transfers heat energy from the first working fluid to a third working fluid;

wherein the membrane contactor extracts a portion of the solvent from the second working fluid; and
wherein the membrane contactor comprises
a first flow channel connected in-line with the first heat exchange circuit, the first flow channel comprising a channel sidewall;
a second flow channel connected in-line with the second heat exchange circuit, the second flow channel comprising a vapor
diffusing membrane; and

a third flow channel that receives vapor of the extracted solvent that migrates across the vapor diffusion membrane from the
first flow channel towards the channel sidewall.

US Pat. No. 9,316,119

TURBOMACHINE SECONDARY SEAL ASSEMBLY

United Technologies Corpo...

1. A turbomachine ring seal assembly, comprising:
a base that extends circumferentially about an axis, the base having an innermost diameter about the axis; and
a protruding element extending radially inward and axially forward from the base,
the protruding element having a first sealing surface that contacts a first support to limit movement of a fluid from a first
axial side of the base to a second opposite axial side of the base, the contact between the first sealing surface and the
first support at a position that is radially inside the innermost diameter of the base,

the protruding element having a second sealing surface that contacts a second support to limit movement of the fluid from
the first axial side of the base to the second opposite axial side of the base, the contact between the second sealing surface
and the second support at a position that is radially inside the innermost diameter of the base,

wherein the first sealing surface faces the axis, and the first sealing surface is transverse to the second sealing surface.

US Pat. No. 9,255,548

SLIDING U-JOINT HANGER FOR GAS TURBINE ENGINE NOZZLE

United Technologies Corpo...

2. A hanger assembly for a gas turbine engine nozzle liner comprising:
a first mount attached to a case;
a second mount attached to the gas turbine engine nozzle liner;
a u-joint including a pivot block movably supported between a first yoke attached to the first mount and a second yoke attached
to the second mount, wherein each of the first yoke and the second yoke are U-shaped and the pivot block includes a first
set of pins received by the first yoke and a second set of pins received by the second yoke, wherein the first set of pins
is disposed transverse to the second set of pins and both the first set of pins and the second set of pins extend outwardly
such that a longitudinal axis of the first set of pins and a longitudinal axis of the second set of pins are disposed within
a common plane.

US Pat. No. 9,255,654

HARD LEAD EGRESS ADAPTER FOR AN INSTRUMENTATION COMPONENT

United Technologies Corpo...

1. An instrumentation component comprising:
an instrumentation portion;
a casing at least partially surrounding said instrumentation portion;
a lead protruding from the instrumentation portion through a lead egress hole in the casing;
a lead egress adapter situated in said lead egress hole, wherein said lead egress adapter includes a cup portion and a lip
portion at least partially circumscribing the cup portion, wherein said lead egress adapter includes a hole in said cup portion,
wherein said lead protrudes through said cup hole and said cup hole is tight fit to said lead, and wherein a potting material
fills a remainder of said cup portion;

wherein said lip portion of said lead egress adapter contacts said casing; and
a lead egress cap sealing said lead egress adapter to said casing, wherein said lead egress cap further comprises a cap hole
through which said lead protrudes, and wherein said cap hole is tight fit to said lead egress;

wherein said lip portion of said lead egress adapter further comprises a tack weld trough circumscribing said cup portion
and wherein said tack weld trough is thinner than a non-tack weld trough portion of said lip portion along an axis defined
by the lead; and

a potting material filling said trough portion.

US Pat. No. 9,181,981

BEARING SYSTEM AND METHOD FOR LUBRICATION

United Technologies Corpo...

1. A bearing system comprising:
a first bearing ring;
a second bearing ring spaced radially outwards from the first bearing ring;
a bearing cage between the first bearing ring and the second bearing ring, the bearing cage including a circumferential outer
side, a circumferential inner side, and circumferentially spaced retainer portions between a first axial end and a second
axial end;

roller elements located in the retainer portions; and
at least one fluid nozzle axially spaced from the bearing cage for providing a fluid to the roller elements, wherein at least
one of the first axial end or the second axial end of the bearing cage includes a scoop protruding axially from the bearing
cage.

US Pat. No. 9,140,187

MAGNETIC DE-ICING

United Technologies Corpo...

1. A turbomachine comprising:
a first member being a nose cone or an inlet cone and having an exposed peripheral surface and an electrically and thermally
conductive portion, an air flowpath passing over the peripheral surface; and

a circumferential array of magnets of alternating polarity mounted for rotation about an axis relative to the first member
inboard of the peripheral surface, the magnets being in sufficient proximity to the electrically and thermally conductive
portions so that the rotation of the magnets about the axis is effective to generate eddy currents, in turn, is effective
to heat the electrically and thermally conductive portion and, thereby, heat the exposed peripheral surface.

US Pat. No. 9,140,214

METHOD OF USING AN AFTERBURNER TO REDUCE HIGH VELOCITY JET ENGINE NOISE

United Technologies Corpo...

1. A method of reducing noise from a turbofan jet engine equipped with an afterburner and a variable area nozzle, the nozzle
having a cross sectional area, the method comprising the steps of:
starting the engine to create exhaust gas flow through the variable area nozzle, the exhaust gas having a temperature, pressure
and velocity at a base state level;

increasing the cross sectional area of the variable area nozzle to increase exhaust gas flow through the variable area nozzle;
lighting the afterburner to increase the exhaust gas temperature; and
retarding engine throttle to lower the engine exhaust gas flow rate;
wherein the afterburner lighting and engine throttle retarding steps reduce exhaust gas pressure to its base state level while
holding exhaust gas velocity at a level above the base state, thereby maintaining engine thrust while reducing engine noise.

US Pat. No. 9,116,051

ACTIVELY COOLED GAS TURBINE SENSOR PROBE HOUSING

United Technologies Corpo...

1. A sensor assembly comprising:
an elongated housing including a proximal end and a distal end portion with a housing body disposed therebetween, the proximal
end including an opening for accommodating a sensor, the sensor extending through the housing body to the distal end portion
of the housing,

the distal end portion of the housing including a port extending generally radially through a trailing side of the distal
end portion, the distal end portion including a leading side disposed diametrically opposite the port and the trailing side
of the distal end portion, and the leading side of the distal end portion curving towards and terminating at the trailing
side of the distal end portion and distally of the port,

the housing body includes a continuous sidewall with a leading plenum extending through the sidewall between the proximal
end and the distal end portion of the housing, the leading plenum being disposed generally diametrically opposite the port,
the housing body further includes a trailing plenum disposed generally diametrically opposite the leading plenum and extending
through the sidewall between the proximal end of the housing and the port.

US Pat. No. 9,097,129

SEGMENTED SEAL WITH SHIP LAP ENDS

United Technologies Corpo...

1. A method of forming a segmented knife edge seal with ship lap ends, the method comprising:
obtaining a plurality of oversized arcuate seal segments, each segment with a first end, a second end, a retention tang to
hold the seal in place with respect to another part, and a main load bearing surface to connect the retention tang to the
knife edge seal, the first and second ends spaced apart in a circumferential direction;

machining the first end of each segment to form a first mating surface for a ship lap seal, wherein machining is performed
on the first end so that the ship lap seal extends through the knife edge seal, and wherein the first end has a convex portion
and a concave portion;

machining the second end of each segment to form a second mating surface for another ship lap seal, wherein machining is performed
on the second end so that the other ship lap seal extends through the knife edge seal, wherein the first mating surface is
complementary and overlapping to the second mating surface when a first end of a seal segment is interfaced with a second
end of another adjacent seal segment, and wherein the second end has a convex portion and a concave portion, the respective
concave and convex portions of the first and second ends defining the complementary ship lap mating surfaces; and

fitting the segments together to form a full circumferential segmented seal, wherein the segments are fit together with the
first mating surface of one segment connecting to the second mating surface of an adjacent segment.

US Pat. No. 9,486,853

CASTING OF THIN WALL HOLLOW AIRFOIL SECTIONS

United Technologies Corpo...

1. A casting mold assembly comprising:
an airfoil defining section including an outer mold wall, and a direct-shelled inner mold wall disposed within a forward chordwise
portion of the airfoil defining section, the direct-shelled inner mold wall including an aft end having an external radius
measuring more than about 0.075 in. (1.9 mm); and

a casting core secured within an aft chordwise portion of the airfoil defining section, the casting core including an aft
end with an external radius measuring less than about 0.075 in. (1.9 mm);

wherein the casting core is disposed aft of the aft end of the direct-shelled inner mold wall, defining a rib portion of the
airfoil defining section aft of a midchord position, the rib mold portion extending generally radially through the casting
mold between the direct-shelled inner mold wall and the casting core.

US Pat. No. 9,404,374

TRUNNION HOLE REPAIR UTILIZING INTERFERENCE FIT INSERTS

United Technologies Corpo...

1. A vane shroud for a gas turbine engine, the vane shroud comprising:
a cylindrical shaped body;
a hole arranged at a circumference of the body, wherein the hole is for receiving a trunnion from a variable vane;
a counterbore arranged concentrically around the hole on a radially inward facing surface of the body, wherein the counterbore
is for receiving a trunnion hub from the variable vane; and

an insert seated into the counterbore such that the trunnion hub is provided with a contact surface; wherein the insert is
secured to the shroud through an interference fit.

US Pat. No. 9,404,735

MULTIPLE LASER TIME OF ARRIVAL PROBE

UNITED TECHNOLOGIES CORPO...

1. A multiple laser time of arrival probe system for stress measurement of rotatable parts, the system comprising:
a laser emission and detection assembly configured to emit a first laser beam and a second laser beam, the first and second
laser beams comprising different wavelengths; and

a probe assembly disposed proximal to a rotatable part in an engine, the probe assembly configured to output a first reflected
laser beam onto a first target on the rotatable part, the probe assembly further configured to output a second reflected laser
beam onto a second target on the rotatable part, the second target different than the first target, the probe assembly including:

a redirector configured to change the first laser beam direction from a first direction to a second direction, and configured
to change the second laser beam direction from a third direction to a fourth direction; and

a lens assembly mounted proximal to the redirector and configured to converge the first laser beam onto the redirector and
to converge the second laser beam onto the redirector.

US Pat. No. 9,350,039

FLOW BATTERY WITH TWO-PHASE STORAGE

United Technologies Corpo...

1. A flow battery comprising:
at least one cell including a first electrode, a second electrode spaced apart from the first electrode, and an electrolyte
separator layer arranged between the first electrode and the second electrode;

at least one storage portion fluidly connected with the at least one cell;
a first reactant material stored within a first storage tank of the at least one storage portion and selectively delivered
to the first electrode of the at least one cell, and the first reactant material is present in a solid phase the least one
storage portion and is present in a liquid phase in the at least one cell;

a second, different reactant material that is circulated through the second electrode with no storage tank;
a feed line having an inlet at the at least one storage portion and an outlet at the at least one cell;
a return line having an inlet at the at least one cell and an outlet at the at least one storage portion; and
a heat exchanger through which the return extends, the heat exchanger operable to control temperature of the reactant material
responsive to an amount of the solid phase, wherein the at least one storage portion, with regard to number of storage portions,
consists of the first storage tank.

US Pat. No. 9,296,039

GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING

UNITED TECHNOLOGIES CORPO...

1. An airfoil comprising:
a body including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil
surface, an exterior wall providing the exterior airfoil surface, an impingement wall integrally formed with the exterior
wall to provide an impingement cavity between the exterior wall and the impingement wall, and multiple impingement holes provided
in the impingement wall, wherein the impingement wall includes a surface from which a first leg extends outward, a second
leg adjoins the first leg at an angle to provide a scoop arranged in a radially extending cooling passage with the second
leg spaced from the surface, the impingement holes include an entrance facing the cooling passage, and an exit facing the
impingement cavity, the scoop arranged at the entrance.

US Pat. No. 9,255,524

VARIABLE OUTER AIR SEAL FLUID CONTROL

United Technologies Corpo...

1. A turbomachine system, comprising: a first variable outer air seal including at least one channel and being configured
to selectively communicate a flow of fluid in response to movement of a second variable outer air seal relative to the first
variable outer air seal, wherein the at least one channel has an inlet, and the second variable outer air seal moves relative
to the inlet between positions that permit flow through the inlet and positions that limit flow through the inlet to selectively
communicate flow.

US Pat. No. 9,181,877

SEAL HOOK MOUNT STRUCTURE WITH OVERLAPPED COATING

UNITED TECHNOLOGIES CORPO...

1. A compressor section for use in a gas turbine engine, comprising:
a compressor blade for rotating about an axis;
a seal positioned radially outwardly of said compressor blade, and said seal having a seal hook facing in a downstream direction;
a seal mount, said seal mount having a mount hook for receiving said seal hook in a gap, and said mount hook facing in an
upstream direction, with said seal mount having an upstream portion extending from an upstream end into said gap, said mount
hook then extending into a web which extends in a downstream direction; and

a thermal barrier coating on said upstream portion of said seal mount from an upstream end and extending to a downstream end,
and there being thermal barrier coating on a radially inner surface of said mount hook, and along said web with an upstream
end of said coating on said radially inner surface of said hook being formed axially upstream of said downstream end of said
coating on said upstream portion.

US Pat. No. 10,053,190

ARTICLE WITH CONTROLLABLE WETTABILITY

United Technologies Corpo...

1. An article with controllable wettability comprising:a substrate;
a layer of a composite material supported on the substrate, the layer having an exposed surface, and the composite material including nanoparticles having controllable polarization embedded fully or partially in a matrix; and
a controller operable to selectively apply a controlled variable activation energy to the layer, the controllable polarization of the nanoparticles varying responsive to the controlled variable activation energy such that a wettability of the exposed surface also varies responsive to the controlled variable activation energy.

US Pat. No. 9,482,115

TURBINE ENGINE SUPPORT ASSEMBLY INCLUDING SELF ANTI-ROTATING BUSHING

United Technologies Corpo...

1. A self anti-rotating bushing component comprising:
a first threaded bushing portion having a first threaded fastener hole and a first extended threading bushing, the first extended
threading bushing having a greater length along an axis defined by the first extended bushing portion than a material tie;

a second threaded bushing portion having a second threaded fastener hole and a second extended threading bushing, the second
extended threading bushing having a greater length along an axis defined by the second extended bushing portion than the material
tie;

the material tie portion connecting said first threaded bushing portion and said second threaded bushing portion; and
wherein said first extended threading bushing has a first radial wall width, said second extended threading bushing has a
second radial wall width, and wherein said first radial wall width is larger than said second radial wall width.

US Pat. No. 9,471,057

METHOD AND SYSTEM FOR POSITION CONTROL BASED ON AUTOMATED DEFECT DETECTION FEEDBACK

UNITED TECHNOLOGIES CORPO...

1. A method of performing position control, the method comprising:
providing a storage medium that stores data and programs used in processing images and a processing unit that processes the
images;

receiving, by the processing unit from an image capture device coupled to the processing unit, a set of video images of a
plurality of members in motion inside of a device;

detecting, by the processing unit, a potential defect in a first member of the plurality of members by performing Robust Principal
Component Analysis to simultaneously decompose the set of video images into a low rank matrix representing the first member
and a sparse matrix representing the potential defect;

implementing, by the processing unit, a classifier to confirm the potential defect is one of a defect or a non-defect;
selecting, by the processing unit, a reference member from the plurality of members inside of the device;
indexing a position of each of the plurality of members inside the device relative to the reference member;
using the indexed positions of each of the plurality of members to locate the first member in a current position; and
after the defect is detected and confirmed in the first member and the first member is located, providing instructions to
move the first member having the defect from the current position to an inspection position in the device.

US Pat. No. 9,376,916

ASSEMBLED BLADE PLATFORM

United Technologies Corpo...

1. A method of making a platform of a blade, the method comprising the steps of:
creating two platform sections by solidifying a material with a fabric in a mold;
positioning a band of fabric around the two platform sections to retain an airfoil and define a blade; and
bonding the two platform sections together by solidifying the material to define a platform of a solid material, wherein the
platform is not bonded to the airfoil.

US Pat. No. 9,371,863

TURBINE ENGINE COUPLING STACK

United Technologies Corpo...

1. A coupling stack comprising:
a first rotating member;
a second rotating member;
a plurality of aligned slots defined in the first rotating member and the second rotating member; and
a tab lock having an annular body with an axial front side and an axial back side, the annular body including:
a plurality of openings extending into a radial inner periphery of the annular body,
a plurality of circumferentially extending flanges on the axial back side of the annular body adjacent to the plurality of
openings, and

a plurality of tabs, each tab formed adjacent a circumferential end of one of the plurality of flanges, wherein at least a
portion of each tab is inserted into one of the plurality of aligned slots.

US Pat. No. 9,303,521

INTERSTAGE COVERPLATE ASSEMBLY FOR ARRANGING BETWEEN ADJACENT ROTOR STAGES OF A ROTOR ASSEMBLY

United Technologies Corpo...

1. An interstage coverplate assembly for a turbine engine rotor assembly including a plurality of bladed rotor stages, each
of the bladed rotor stages including a plurality of rotor blades connected to a rotor disk, the assembly comprising:
an annular first coverplate including a plurality of coverplate tabs arranged circumferentially around an axial centerline,
wherein the first coverplate is configured to engage a first of the bladed rotor stages;

an annular second coverplate configured to engage a second of the bladed rotor stages; and
an annular coverplate lock extending axially between and rotatably connecting the first and the second coverplates, the coverplate
lock including a plurality of lock tabs arranged circumferentially around the centerline, wherein a first of the lock tabs
circumferentially engages a first of the coverplate tabs.

US Pat. No. 9,228,448

BACKGROUND RADIATION MEASUREMENT SYSTEM

United Technologies Corpo...

1. A turbine section comprising:
an airfoil including an edge;
a probe positioned a distance from the airfoil configured to detect radiation emitted from a radiation source; and
a sensor operatively coupled to the probe and configured to generate a signal utilized to determine when the edge of the airfoil
extends into a line-of-sight between the probe and the radiation source, wherein the radiation source emits radiation at a
first range of amplitudes and the airfoil emits radiation at a second range of amplitudes different from the first range of
amplitudes.

US Pat. No. 9,206,775

FUEL PREHEATING USING ELECTRIC PUMP

United Technologies Corpo...

1. A fuel system for an auxiliary power unit, the fuel system comprising:
a mechanical fuel pump for providing fuel flow to the auxiliary power unit, the mechanical fuel pump having an output dependent
upon an operational speed of the auxiliary power unit;

an electric fuel pump located in series with the mechanical fuel pump, wherein the electric fuel pump is located upstream
of the mechanical fuel pump on a common fuel supply conduit, wherein the electric fuel pump is driven independently of the
operational speed of the auxiliary power unit;

a relief fuel conduit having a first end and a second end, the first end fluidly connected to the fuel supply conduit downstream
of the electric fuel pump and the second end fluidly connected to the fuel supply conduit upstream of the electric fuel pump;

a relief check valve located on the relief fuel conduit, the check valve having an open configuration for allowing fuel to
flow from the first end to the second end of the relief fuel conduit; and

a controller configured to cause the electric fuel pump to circulate fuel from the first end to the second end of the relief
fuel circuit prior to start-up of the auxiliary power unit.

US Pat. No. 9,181,898

THRUST REVERSER FOR A GAS TURBINE ENGINE WITH MOVEABLE DOORS

United Technologies Corpo...

1. A thrust reverser for a gas turbine engine comprising:
an actuator shaft;
a slider movable along said actuator shaft;
an inner thrust reverser door;
an outer thrust reverser door, wherein said inner thrust reverser door is pivotable in an opposite direction relative to said
outer thrust reverser door to pivot away from said outer thrust reverser door when moved toward a thrust reverse position;

an inner linkage mounted to said slider and said inner thrust reverser door;
an outer linkage mounted to said slider and said outer thrust reverser door, wherein said inner linkage is of a different
length than said outer linkage; and

a thrust reverser cascade, said actuator shaft at least partially extending axially through said thrust reverser cascade.

US Pat. No. 9,097,138

GAS TURBINE ENGINE BUFFER SYSTEM

United Technologies Corpo...

1. A gas turbine engine, comprising:
a compressor section;
a combustor in fluid communication with said compressor section;
a turbine section in fluid communication with said combustor;
a buffer system including a first circuit that supplies a first buffer supply air and a second circuit that supplies a second
buffer supply air;

wherein said first circuit includes a first bleed air supply, a second bleed air supply and at least one of an ejector and
a valve; and

wherein said second circuit includes a third bleed air supply, a fourth bleed air supply and at least one of an ejector and
a valve.

US Pat. No. 9,091,173

TURBINE COOLANT SUPPLY SYSTEM

United Technologies Corpo...

12. A method of providing compressor bleed air to a turbine stage of a gas turbine engine, the method comprising:
flowing the bleed air axially along a shaft connecting a compressor stage to a turbine stage, wherein an inner diameter bore
of a rotor disk and the shaft define a cavity;

passing the bleed air through the cavity;
directing the bleed air radially along an aft surface of the rotor disk; and
feeding the bleed air into a blade slot in a rim of the rotor disk.

US Pat. No. 9,080,594

REMOVABLE SELF-LOCKING PLUG

United Technologies Corpo...

1. A self-locking plug, comprising:
a sleeve having an anti-rotation feature for reducing axial rotation of the sleeve during at least one of core removal and
core installation;

a core extending through the sleeve; and
a lock carried between the sleeve and the core, the lock including
a first component having a protrusion that extends radially out to a circumferentially extending interference surface; and
a second component having a cantilevered interference tab that is radially biased against the interference surface.

US Pat. No. 9,534,507

HARNESS SUPPORT AND MOUNT

United Technologies Corpo...

1. A harness assembly comprising:
a base including a mounting surface and an opening;
a harness clamp including a mount end receivable within the opening and a lockable clip, the opening including a first securement
feature and the mount end including a second securement feature engageable with the first securement feature for holding the
harness in a fixed orientation relative to the base, wherein the harness clamp includes first splines extending longitudinally
about an inner surface of the opening and second splines extending longitudinally along the mount end, the second splines
engagable with the first splines for defining a rotational orientation of the harness relative to the base.

US Pat. No. 9,470,153

COMBINED PUMP SYSTEM FOR ENGINE TMS AOC REDUCTION AND ECS LOSS ELIMINATION

UNITED TECHNOLOGIES CORPO...

1. A compression pump for an engine, comprising:
a first radial pump impeller operatively coupled to a main shaft of the engine, the first radial pump impeller rotatably fixed
about a common axis of the compression pump, the common axis of the compression pump nonparallel to a center axis of the engine;

a first inlet configured to at least partially receive bypass airflow; a first outlet configured to direct compressed air
to a thermal management system;

wherein the first radial pump impeller is coupled to the main shaft by an engine towershaft and wherein the engine towershaft
rotatable about a longitudinal axis; and

wherein the compression pump is located within an engine core nacelle of the engine.

US Pat. No. 9,421,661

AIRFOIL EDGE FORM TRANSFER GRINDING TOOL

UNITED TECHNOLOGIES CORPO...

1. A grinding tool for an airfoil comprising:
an axial grinding wheel having a circumferential cutting slot formed therein, the cutting slot being configured to form a
finished radiused edge of the airfoil, the slot having a cross-sectional profile that includes a floor having a first radius
of curvature, a first side wall rising upward from the floor and having a second radius of curvature, and a second side wall
rising upward from the floor opposite the first side wall and having a third radius of curvature, wherein the first radius
of curvature is different from the second radius of curvature and the third radius of curvature is different from the first
radius of curvature and the second radius of curvature.

US Pat. No. 9,353,644

SYNCHRONIZING RING SURGE BUMPER

United Technologies Corpo...

16. A gas turbine engine comprising:
an engine case;
a section, selected from the group consisting of a compressor and a turbine, having at least a first stage of variable guide
vanes circumferentially spaced radially inward of the engine case;

a synchronizing ring assembly comprising split rings and being disposed about the engine case and connected to the first stage
of variable guide vanes; and

a surge bumper assembly connected to a first side surface of the synchronizing ring assembly and extending axially adjacent
of an inner radial surface of the synchronizing ring assembly, wherein the surge bumper assembly is disposed adjacent a gap
at an end of one of the ring sections.

US Pat. No. 9,187,815

THERMAL STABILIZATION OF COATING MATERIAL VAPOR STREAM

United Technologies Corpo...

1. A coating system comprising:
a work piece;
a coating delivery apparatus configured to apply a coating material to the work piece in a plasma-based vapor stream;
a first electron gun configured to direct a first electron beam at the plasma-based vapor stream at a region of the plasma-based
vapor stream that extends from a location downstream from the coating delivery apparatus where the coating material transitions
to vapor phase to a location upstream from the work piece for adding thermal energy to the coating material in the plasma-based
vapor stream, wherein the first electron gun is further configured to scan the first electron beam across at least a portion
of the region of the plasma-based vapor stream; a susceptor positioned adjacent to the work piece; and

a susceptor-directed electron gun configured to direct an electron beam at the susceptor such that the susceptor radiates
heat toward the work piece.

US Pat. No. 9,166,243

FLOW BATTERY WITH INTERDIGITATED FLOW FIELD

United Technologies Corpo...

1. A redox flow battery comprising:
a first liquid-porous electrode;
a second liquid-porous electrode spaced apart from the first liquid-porous electrode;
an ion-exchange membrane arranged between the first liquid-porous electrode and the second liquid-porous electrode;
first and second flow fields adjacent the respective first liquid-porous electrode and second liquid-porous electrode, each
of the first and second flow fields including first channels having at least partially blocked outlets and second channels
having at least partially blocked inlets, and the second channels are interdigitated with the first channels; and

a positive electrolyte storage tank connected in a positive recirculation loop with one of the first or second flow fields
and a negative electrolyte storage tank connected in a negative recirculation loop with the other of the first or second flow
fields.

US Pat. No. 9,163,717

MULTI-PIECE FLUID MANIFOLD FOR GAS TURBINE ENGINE

United Technologies Corpo...

1. A gas turbine engine comprising:
a first shaft that interconnects a fan, a low pressure compressor, and a low pressure turbine;
a second shaft that interconnects a high pressure compressor and a high pressure turbine, the second shaft configured to rotate
at a faster speed than the first shaft;

a geared architecture that interconnects the first shaft to drive the fan, the geared architecture comprising a gear assembly
enclosed within a gear housing;

a manifold assembly comprising a mounting plate having a mount interface attached to the gear housing and a flow plate attached
to the mounting plate to provide a plurality of flow passages between the mounting plate and flow plate, the manifold assembly
including at least one fluid inlet configured to receive fluid from a supply and at least one fluid outlet to direct the fluid
into the gear housing;

wherein the flow plate comprises a ring-shaped structure with a center opening defining a center axis and a first ring portion
defined by a first inner peripheral surface extending circumferentially about the axis and a first outer peripheral surface
spaced radially outwardly relative to the first inner peripheral surface;

wherein the mounting plate comprises a ring-shaped structure with a center opening concentric with the center axis and a second
ring portion defined by a second inner peripheral surface extending circumferentially about the axis and a second outer peripheral
surface spaced radially outwardly relative to the second inner peripheral surface; and

wherein the plurality of flow passages comprises at least a first flow passage formed adjacent to the first and second inner
peripheral surfaces and a second flow passage formed adjacent to the first and second outer peripheral surfaces, the first
and second flow passages extending circumferentially around the first and second ring portions to at least partially surround
the central axis.

US Pat. No. 9,163,562

CONSTANT SPEED PUMP SYSTEM FOR ENGINE ECS LOSS ELIMINATION

United Technologies Corpo...

1. A gas turbine engine comprising:
a fan configured to produce propulsive thrust from a fan discharge air stream,
a bypass duct located between a cowl and an engine core, said bypass duct fluidly coupled to said fan;
an impeller pump positioned on said engine core, said impeller pump having an intake manifold fluidly coupled to said bypass
duct and configured to intake a portion of said fan discharge air stream, said impeller pump having an outlet coupled to an
outlet duct fluidly coupled to an environmental control system, wherein said impeller pump is configured to raise pressure
of said portion of said fan discharge air stream and pump said portion of said fan discharge air stream into said environmental
control system for cooling;

an integrated drive pump connected to said impeller pump for driving said impeller pump at a constant speed, said integrated
drive pump being positioned on said engine core, said integrated drive pump being connected to a towershaft opposite said
impeller pump for driving said integrated drive pump.

US Pat. No. 9,097,133

COMPRESSOR TIP CLEARANCE MANAGEMENT FOR A GAS TURBINE ENGINE

UNITED TECHNOLOGIES CORPO...

1. A method of managing a tip clearance in a high pressure compressor on a high spool, wherein a low spool includes a low
pressure compressor, comprising the steps of:
identifying a high pressure compressor clearance condition; and
adjusting a variable stator vane arranged upstream from the high pressure compressor and in the low pressure compressor;
thereby altering a high pressure compressor rotor speed with the variable stator vane for changing the high pressure compressor
clearance condition.

US Pat. No. 9,726,019

LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE

UNITED TECHNOLOGIES CORPO...

1. A gas turbine engine comprising:
a fan, a turbine section having a fan drive turbine rotor, and a compressor rotor;
a gear reduction effecting a reduction in a speed of said fan relative to an input speed from said fan drive turbine rotor;
said compressor rotor having a number of compressor blades in at least one of a plurality of blade rows of said compressor
rotor, and said blades configured to operate at least some of the time at a rotational speed, and said number of compressor
blades in said at least one of said blade rows and said rotational speed being such that the following formula holds true
for said at least one of said plurality of blade rows of the compressor rotor:

(said number of blades×said rotational speed)/60 sec?about 5500 Hz; and
said rotational speed being an approach speed in revolutions per minute.

US Pat. No. 9,476,307

CASTINGS, CASTING CORES, AND METHODS

United Technologies Corpo...

1. A gas turbine engine component comprising:
an airfoil having:
a leading edge;
a trailing edge;
a pressure side extending between the leading edge and trailing edge;
a suction side extending between the leading edge and trailing edge; and
one or more cooling passageways extending through the airfoil and comprising a trunk extending from an inlet,wherein:
at said inlet, said trunk is at least partially surrounded by an additional passageway, said additional passageway having
a concavity with a spanwise axis of curvature, with a surface of the additional passageway adjacent the trunk having concavity
facing the trunk; and

in transverse section, the at least one additional passageway bends by at least 45°.

US Pat. No. 9,429,027

TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING

United Technologies Corpo...

1. An airfoil comprising:
a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil;
a leading edge and a trailing edge defining a chord length of the airfoil therebetween; and
a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall, wherein the tip
shelf wall is spaced between the pressure surface and the suction surface, wherein the tip shelf extends from within 10% of
the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge; wherein
the tip shelf extends around the leading edge and onto the suction surface to terminate on the suction surface between the
leading edge and the trailing edge of the airfoil; wherein the leading edge further comprises an indentation formed on the
leading edge, the indentation extending along the leading edge between the root section of the airfoil and the tip section
of the airfoil, and wherein the indentation intersects the tip shelf at the leading edge; wherein the tip shelf extends to
the trailing edge of the airfoil to terminate at a downstream intersection of the pressure and suction surfaces such that
the tip shelf communicates with both the pressure surface and the suction surface proximate to the trailing edge.

US Pat. No. 9,394,915

SEAL LAND FOR STATIC STRUCTURE OF A GAS TURBINE ENGINE

United Technologies Corpo...

1. A seal land for a gas turbine engine, comprising:
a seal body mounted to a platform of a gas turbine engine component, said seal body extending between a leading edge portion,
a trailing edge portion, a radially outer surface and a radially inner surface, and said seal body is tapered from said trailing
edge portion to said leading edge portion; and

a notch that extends at least partially through said seal body between said radially outer surface and said radially inner
surface and extending from one of said leading edge portion and said trailing edge portion toward the other of said leading
edge portion and said trailing edge portion, and a first thickness of said seal body extends radially outward of said notch
and a second, different thickness of said seal body extends radially inward of said notch.

US Pat. No. 9,388,700

GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT

UNITED TECHNOLOGIES CORPO...

1. An airfoil for a gas turbine engine, comprising:
an airfoil body that extends between a leading edge and a trailing edge; and
a cooling circuit defined within said airfoil body, wherein said cooling circuit includes at least one trip strip disposed
within a cavity of said cooling circuit between a leading edge inner wall and a first rib, wherein said at least one trip
strip includes an increasing height in a direction from said first rib toward said leading edge inner wall.

US Pat. No. 9,341,377

SPHERICAL COLLET FOR MOUNTING A GAS TURBINE ENGINE LINER

United Technologies Corpo...

1. A liner and attachment structure comprising:
an exhaust liner exposed to exhaust gases within a gas turbine engine;
at least one hanger, said at least one hanger having feet which are secured to said exhaust liner, and said at least one hanger
having an aperture at a central web of said at least one hanger;

a flanged washer received within said aperture in said at least one hanger, and said flanged washer is adjustable relative
to said at least one hanger, said flanged washer having a spherical recess;

a collet having a plurality of part-spherical fingers separated by slots, with said plurality of part-spherical fingers received
in said spherical recess of said flanged washer, and a member extending into said collet to hold said plurality of part-spherical
fingers radially outwardly, and said member also being secured to a static structure, to secure said exhaust liner to the
static structure,

wherein an outer periphery of said collet has threads that are adjustable relative to the static structure and said exhaust
liner.

US Pat. No. 9,243,502

AIRFOIL COOLING ENHANCEMENT AND METHOD OF MAKING THE SAME

UNITED TECHNOLOGIES CORPO...

1. A method of manufacturing an airfoil comprising the steps of:
depositing multiple layers of powdered metal onto one another;
joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil; and
producing the airfoil with leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior
airfoil surface, a cooling passage arranged interiorly of the exterior airfoil surface and providing an interior surface,
the interior cooling surface including micro-bumps protruding from the interior cooling surface into the cooling passage,
the micro-bumps discrete from and noncontiguous relative to one another in multiple directions along the interior cooling
surface, wherein the micro-bumps are noncontiguous from one another 360° about each micro-bump along the interior cooling
surface.

US Pat. No. 9,212,560

CMC BLADE WITH INTEGRAL 3D WOVEN PLATFORM

UNITED TECHNOLOGIES CORPO...

1. A method of forming a component for use in a gas turbine engine comprising the steps of:
forming an airfoil/root assembly;
creating a platform assembly structure from a three dimensional woven material having an opening;
inserting said airfoil/root assembly into said opening; and
bonding said platform assembly structure to said airfoil/root assembly to form said component, wherein the bonding step is
carried out by introducing a bonding agent, which after bonding creates an interfacial layer between the airfoil/root assembly
and the platform assembly structure.

US Pat. No. 9,097,350

AXIAL NON-CONTACT SEAL

United Technologies Corpo...

1. A gas turbine engine comprising:
a turbine section and an air moving section upstream of the turbine section; and
a seal between a static surface and a rotating surface in at least one of said turbine section and said air moving section;
said seal including a seal shoe which is biased at least in part by a spring force, with said spring force created by cuts
formed to provide a gap to allow arms associated with said seal to provide said spring force, and the movement of said shoe
being along a direction having at least a component parallel to an axis of rotation of the gas turbine engine; and

wherein the movement of said shoe is one of directly parallel to said axis of rotation, or the movement of said shoe also
having a radial component, and said seal sealing on a generally conical shaped surface.

US Pat. No. 9,097,122

TURBINE ENGINE MONITORING SYSTEM

United Technologies Corpo...

1. A turbine engine system, comprising:
a turbine engine shaft comprising a shaft bore formed by a shaft wall, the shaft bore extending along an axial centerline
through the turbine engine shaft between a first shaft end and a second shaft end;

a first rotor connected to the turbine engine shaft at the first shaft end;
a second rotor connected to the turbine engine shaft at the second shaft end; and
an engine monitoring system comprising a sensor connected to the second rotor, a transmitter arranged at the first shaft end,
and a plurality of conduit assemblies, wherein each of the plurality of conduit assemblies comprises a conduit extending axially
within the shaft bore and connected to the shaft wall, and a first of the plurality of conduit assemblies further comprises
a wire extending through the respective conduit and connecting the sensor and the transmitter.

US Pat. No. 9,433,957

COLD SPRAY SYSTEMS WITH IN-SITU POWDER MANUFACTURING

UNITED TECHNOLOGIES CORPO...

15. A cold spray system, comprising:
a powder generator having a powder source disposed within a housing;
a classifier for removing particles outside of a predetermined size range from a particle flow received from powder generator;
a feedstock hopper for storing particles received from the classifier to regulate between a particle production rate of the
powder generator and a particle usage rate of the powder feeder; and

a powder feeder for feeding a consistent flow of particles received from the feedstock hopper, wherein a closed circuit with
an inert atmosphere is defined from the powder generator to the powder feeder including the classifier and feedstock hopper
for conveying powder from the powder generator to the powder feeder without exposing the powder to contaminates from outside
the closed circuit.

US Pat. No. 9,415,438

METHOD FOR FORMING SINGLE CRYSTAL PARTS USING ADDITIVE MANUFACTURING AND REMELT

United Technologies Corpo...

1. A method of forming a metal single crystal turbine component with internal passageways comprising:
forming a polycrystalline metal turbine component with internal passageways by an additive manufacturing process;
filling the internal passageways with a core ceramic slurry;
treating the ceramic slurry to form a ceramic core;
encasing the metal component in a ceramic shell;
treating the ceramic shell to form a ceramic mold;
placing the ceramic mold in a furnace and melting the metal turbine component;
directionally solidifying the melt to form a metal single crystal turbine; and
cooling the mold, removing the outer shell and inner ceramic core to reveal a finished metal single crystal turbine component
with internal passageways.