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US 8,776,525 B2Granted
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.
Claims16
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 configured to generate a primary combustion zone having a recirculation vortex within the single-sided recirculation combustor,
- wherein the single-sided recirculation combustor includes a tubular compressor discharge air injector having an inlet exposed to the total pressure of the air exiting the compressor, and wherein the compressor discharge air injector is configured to discharge pressurized air into the recirculation vortex;
- and
- wherein the single-sided recirculation combustor includes an air scoop disposed downstream of the tubular compressor discharge air injector, and wherein the air scoop is configured to confine the vortex.
4 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 combustion zone of the recirculation combustor,
- wherein the compressor discharge air injector is positioned on the recirculation combustor to receive the total pressure of the air discharged by the compressor, wherein the recirculation combustor is configured to generate the primary combustion zone having a recirculation vortex therein;
- and wherein the compressor discharge air injector is configured to discharge pressurized air into the recirculation vortex;
- wherein the recirculation combustor includes an air scoop disposed downstream of the compressor discharge air injector;
- and
- wherein the air scoop is configured to confine the vortex.
8 more elements
Dependencies are inferred from the claim text.