All CO2 aircraft
First Claim
Patent Images
1. An aircraft power and propulsion system, comprising:
- an air compressor;
a heat rejection heat exchanger;
a combustor positioned to receive compressed air from the air compressor as a core stream and provide thrust to the aircraft power and propulsion system; and
a closed-loop s-CO2 system having carbon dioxide as a working fluid, that receives power from the combustor and rejects heat via the heat rejection heat exchanger to a cooling stream, the closed-loop s-CO2 system is configured to provide power to;
a fan that provides the cooling stream and thrust;
the air compressor; and
at least one auxiliary load;
wherein the closed-loop system further comprises;
a first s-CO2 turbine coupled to an s-CO2 compressor via a first shaft;
a second s-CO2 turbine coupled to the air compressor via a second shaft; and
a third s-CO2 turbine coupled to the fan via a third shaft; and
wherein the first shaft, the second shaft, and the third shaft are axially offset from each other.
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Abstract
An aircraft power and propulsion system includes an air compressor, a heat rejection heat exchanger, a combustor positioned to receive compressed air from the air compressor as a core stream and provide thrust to the aircraft, and a closed-loop s-CO2 system. The closed-loop s-CO2 system includes carbon dioxide as a working fluid, receives power from the combustor, and rejects heat via the heat rejection heat exchanger to a cooling stream. The closed-loop system s-CO2 configured to provide power to a fan that provides the cooling stream and thrust, and power to the air compressor and at least one auxiliary load.
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Citations
19 Claims
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1. An aircraft power and propulsion system, comprising:
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an air compressor; a heat rejection heat exchanger; a combustor positioned to receive compressed air from the air compressor as a core stream and provide thrust to the aircraft power and propulsion system; and a closed-loop s-CO2 system having carbon dioxide as a working fluid, that receives power from the combustor and rejects heat via the heat rejection heat exchanger to a cooling stream, the closed-loop s-CO2 system is configured to provide power to; a fan that provides the cooling stream and thrust; the air compressor; and at least one auxiliary load; wherein the closed-loop system further comprises; a first s-CO2 turbine coupled to an s-CO2 compressor via a first shaft; a second s-CO2 turbine coupled to the air compressor via a second shaft; and a third s-CO2 turbine coupled to the fan via a third shaft; and wherein the first shaft, the second shaft, and the third shaft are axially offset from each other. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A method of providing power via an aircraft power and propulsion system, comprising:
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receiving compressed air from an air compressor as a core stream to provide thrust to the aircraft power and propulsion system; providing power in a closed-loop s-CO2 system, having carbon dioxide as a working fluid, to; a fan that provides a cooling stream and thrust to the aircraft; the air compressor; and at least one auxiliary load; and rejecting heat from the closed-loop s-CO2 system via a heat rejection heat exchanger to the cooling stream; wherein the closed-loop system further comprises; a first s-CO2 turbine coupled to an s-CO2 compressor via a first shaft; a second s-CO2 turbine coupled to the air compressor via a second shaft; and a third s-CO2 turbine coupled to the fan via a third shaft; and wherein the first shaft, the second shaft, and the third shaft are axially offset from each other. - View Dependent Claims (9, 10, 11, 12, 13)
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14. A power-producing device for an aircraft, comprising:
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an air compressor; a heat rejection heat exchanger configured to reject heat from a working fluid of a closed-loop s-CO2 system; a combustor positioned to receive compressed air from the air compressor as a core stream and provide thrust to the aircraft; and the closed-loop s-CO2 system having carbon dioxide as the working fluid, that receives power from the combustor and rejects heat via the heat rejection heat exchanger to a cooling stream, the closed-loop system s-CO2 configured to provide power to; a fan that provides the cooling stream and thrust to the aircraft; the air compressor; and at least one auxiliary load; wherein the closed-loop system further comprises; a first s-CO2 turbine coupled to an s-CO2 compressor via a first shaft; a second s-CO2 turbine coupled to the air compressor via a second shaft; and a third s-CO2 turbine coupled to the fan via a third shaft; and wherein the first shaft, the second shaft, and the third shaft are axially offset from each other. - View Dependent Claims (15, 16, 17, 18, 19)
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Specification