US Patent No. 10,690,345

COMBUSTOR ASSEMBLIES FOR USE IN TURBINE ENGINES AND METHODS OF ASSEMBLING SAME


Patent No. 10,690,345
Issue Date June 23, 2020
Title Combustor Assemblies For Use In Turbine Engines And Methods Of Assembling Same
Inventorship Joseph Douglas Monty, Boxford, MA (US)
John Carl Jacobson, Melrose, MA (US)
Stephen John Howell, West Newbury, MA (US)
Assignee General Electric Company, Schenectady, NY (US)

Claim of US Patent No. 10,690,345

1. A reverse flow combustor assembly for use in a gas turbine engine, the combustor assembly comprising:a combustor liner defining a combustion chamber and comprising an axial combustion portion and a curved transition portion, the curved transition portion positioned between an inlet and outlet of the combustor liner such that the inlet and outlet are spaced-apart along a curved centerline, wherein the combustor liner comprises an inner surface and an outer surface and a first plurality of cooling channels defined between the inner and outer surfaces; and
a sleeve substantially circumscribing the combustor liner such that an annular cavity is defined between the combustor liner and the sleeve, wherein the sleeve comprises a second plurality of cooling channels defined therethrough, the second plurality of cooling channels configured to channel a fluid against the combustor liner outer surface;
a single solid partition positioned within the cavity between the combustor liner and the sleeve, the partition being positioned axially between the axial combustion portion and the transition portion such that the partition extends circumferentially about an entirety of the combustor liner within the cavity to define a first cooling zone within the cavity upstream of the partition and a second cooling zone within the cavity downstream of the partition, the partition causing a differential pressure between the first and the second cooling zones.