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US 6,182,451 B2Granted
Gas turbine combustor waving ceramic combustor cans and an annular metallic combustor
AssigneeAlliedSignal Inc.
InventorJames L. Hadder
Life of this patent
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Abstract
A hybrid combustor for a gas turbine engine includes a plurality of circularly arrayed ceramic can combustors whose outlets communicate with the inlet of an annular, metal combustor. The combustion process is continuous through the plurality of can combustors and into the single annular combustor. Preferably only fuel-rich combustion occurs within each of the can combustors, and fuel-lean combustion continues within the single annular combustor.
Claims11
A gas turbine engine combustor comprising:
- an annular casing having a pressurized air inlet, an exhaust, and a fuel supply duct;
- a plurality of thin wall, ceramic, can combustors in said casing receiving air from said inlet and fuel from said fuel duct to establish combustion within said can combustors, each of said can combustors including a continuous, non-perforated, cylindrical ceramic wall;
- and
- a metallic, annular combustor between said can combustors and said exhaust, said annular combustor receiving air from said inlet and combustion products from said can combustors to continue said combustion within said annular combustor,
- said can combustors and said annular combustor relatively arranged and configured whereby substantially only fuel-rich combustion occurs in each of said can combustors and substantially only fuel-lean combustion occurs in said annular combustor, and whereby the flame front of said fuel rich combustion in each of said can combustors extends into said annular combustor such that said fuel-lean combustion in said annular combustor is a continuation of said fuel-rich combustion.
2 more elements
Dependencies are inferred from the claim text.