Engine driven by Sc02 cycle with independent shafts for combustion cycle elements and propulsion elements
First Claim
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1. A gas turbine engine, comprising:
- a first shaft coupled to a first turbine and a first compressor;
a second shaft offset axially from the first shaft, the second shaft coupled to a second turbine and a second compressor;
a heat rejection heat exchanger configured to reject heat from a closed loop system to bypass air of the gas turbine engine;
a combustor configured to combust air from the second compressor;
wherein the closed-loop system;
includes the first and second turbines and the first compressor;
receives energy input from the combustor; and
provides power from the combustor to the first and second turbines.
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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.
49 Citations
20 Claims
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1. A gas turbine engine, comprising:
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a first shaft coupled to a first turbine and a first compressor; a second shaft offset axially from the first shaft, the second shaft coupled to a second turbine and a second compressor; a heat rejection heat exchanger configured to reject heat from a closed loop system to bypass air of the gas turbine engine; a combustor configured to combust air from the second compressor;
wherein the closed-loop system;includes the first and second turbines and the first compressor; receives energy input from the combustor; and provides power from the combustor to the first and second turbines. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A method of providing power is a gas turbine engine, comprising:
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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 combust the core stream of air in the combustor; and passing the working fluid from the combustor to provide power to a fan assembly that provides both the core stream of air to the second compressor, and provides a cooling stream of air to the heat rejection heat exchanger; wherein the closed-loop system; includes the first and second turbines and the first compressor; receives energy input from the combustor; and provides power from the combustor to the first and second turbines. - View Dependent Claims (10, 11, 12, 13, 14, 15, 16)
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17. 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, the second shaft axially offset from the first shaft; a combustor configured to combust air from the second compressor; and a heat rejection heat exchanger configured to reject heat from a closed loop system to bypass air that is passed from a fan assembly; wherein the closed-loop system; includes the first and second turbines and the first compressor; receives energy input from the combustor; and provides power from the combustor to the first and second turbines. - View Dependent Claims (18, 19, 20)
Specification