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US 2012/0233980 A1Published application
Variable cycle gas turbine engine
AssigneeRolls-Royce North American Technologies Inc.
InventorCraig Heathco
Life of this patent
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Abstract
One embodiment of the present invention is a unique variable cycle gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for variable cycle gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
Claims20
A variable cycle gas turbine engine, comprising:
- a compressor configured to compress a core gas flow;
- a combustor in fluid communication with the compressor and configured to combust the core gas flow;
- a primary turbine drivingly coupled to the compressor and configured to receive the core gas flow, wherein the primary turbine is configured to drive the compressor;
- an auxiliary turbine drivingly coupled to the compressor;
- and
- a valve configured to selectively direct a portion of the core gas flow to the auxiliary turbine,
- wherein the auxiliary turbine is configured to extract power from the portion of the core gas flow and supply the power to the compressor when the valve is open.
4 more elements
A variable cycle gas turbine engine, comprising:
- a compressor configured to compress a core gas flow;
- a combustor in fluid communication with the compressor and configured to combust the core gas flow;
- a primary turbine drivingly coupled to the compressor and configured to receive the core gas flow, wherein the primary turbine is configured to drive the compressor;
- and
- an auxiliary turbine system having an auxiliary turbine drivingly coupled to the compressor, wherein the auxiliary turbine system is configured to selectively receive a portion of the core gas flow;
- generate shaft power using the portion of the core gas flow;
- and supply the shaft power to the compressor.
4 more elements
A variable cycle gas turbine engine, comprising:
- a compressor configured to compress a core gas flow;
- a combustor in fluid communication with the compressor and configured to combust the core gas flow;
- a turbine drivingly coupled to the compressor and configured to receive the core gas flow, wherein the turbine is configured to drive the compressor;
- and
- means for selectively expanding and contracting a turbine flow capacity.
2 more elements
Dependencies are inferred from the claim text.