Engine driven by SC02 cycle with independent shafts for combustion cycle elements and propulsion elements
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc.
InventorsMichael J. Armstrong, Igor Vaisman
Life of this patent
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Abstract
A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.
Claims19
A gas turbine engine, comprising:
- a first shaft coupled to a first turbine and a first compressor;
- a second shaft coupled to a second turbine and a second compressor;
- a third shaft coupled to a third turbine and a fan assembly;
- a heat rejection heat exchanger configured to reject heat from a closed loop system with bypass air passed from the fan assembly to provide cooling to the heat rejection heat exchanger;
- a combustor positioned to receive compressed air from the second compressor as a core stream;
- wherein the closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor;
- and
- wherein the closed-loop system is configured to provide power from the combustor to the first, second, and third turbines.
A method of providing power via a gas turbine engine, comprising:
- powering a first shaft via a closed loop system that passes a working fluid from a first compressor to a combustor, receives power from combustion in the combustor, passes the working fluid from the combustor to a first turbine, and cools the working fluid with bypass air in a heat rejection heat exchanger;
- passing the working fluid from the combustor and powering a second shaft using a second turbine of the closed loop system that is coupled to the second shaft, to provide a core stream of air via a second compressor to the combustor;
- and
- passing the working fluid from the combustor and powering a third shaft using a third turbine of the closed loop system that is coupled to the third shaft, to provide power to a fan assembly that provides both the core stream of air to the second compressor, and to provide a cooling stream of air to the heat rejection heat exchanger;
- wherein the closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor;
- and
- wherein the closed-loop system is configured to provide power from the combustor to the first, second, and third turbines.
A power-producing device, comprising:
- an inner housing for passing a core stream of air, the inner housing houses:
- a first shaft coupled to a first turbine and a first compressor;
- a second shaft coupled to a second turbine and a second compressor;
- a third shaft coupled to a third turbine and a fan assembly;
- a combustor positioned to receive compressed air from the second compressor;
- and
- a heat rejection heat exchanger configured to reject heat from a closed loop system with bypass air passed from a fan assembly to provide cooling to the heat rejection heat exchanger;
- wherein the closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor;
- and
- wherein the closed-loop system is configured to provide power from the combustor to the first, second, and third turbines.
Dependencies are inferred from the claim text.