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US 2012/0067051 A1Published application
Gas turbine engine and combustor
AssigneeRolls-Royce North American Technologies Inc.
InventorVictor L. Oechsle
Life of this patent
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Abstract
The present invention provides in one embodiment a unique gas turbine engine. Another embodiment is a unique gas turbine engine combustion system. Still another embodiment is a unique gas turbine engine combustor. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine combustion systems and combustors.
Claims24
A gas turbine engine, comprising:
- a compressor;
- a turbine;
- and
- a combustion system in fluid communication with the compressor and the turbine, wherein the combustion system includes a slinger injector and a single-sided recirculation combustor.
1 more element
A gas turbine engine, comprising:
- a compressor;
- a turbine;
- means for containing a combustion process;
- and
- means for introducing fuel into the means for containing.
2 more elements
A gas turbine engine combustion system, comprising:
- a recirculation combustor operative to receive pressurized air from a gas turbine engine compressor and discharge combustion products to a gas turbine engine turbine, including:
- an outer annular combustion liner;
- an annular end wall;
- a continuous annular fuel injection zone;
- and
- a compressor discharge air injector that extends inside of the recirculation combustor from one or both of the outer annular combustion liner and the annular end wall, wherein the compressor discharge air injector is operative to initiate a recirculation vortex in a primary zone of the recirculation combustor.
3 more elements
Dependencies are inferred from the claim text.