Gas turbine engine with transcritical vapor cycle cooling
A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.
1. A gas turbine engine comprising:
a compressor section;
a combustor;
a turbine section;
a fuel supply system for supplying fuel to said combustor, and including a fuel heating heat exchanger, with a bypass line downstream of said fuel heating heat exchanger for bypassing fuel back to a fuel tank;
fuel in said bypass line being a fluid to be cooled;
an associated fluid to be heated; and
a transcritical vapor cycle for heating said fluid to be heated, and for cooling said fluid to be cooled, said transcritical vapor cycle including:
a gas cooler, in which said fluid to be heated is heated by a refrigerant in said transcritical vapor cycle;
an evaporator heat exchanger at which said fluid to be cooled is cooled by the refrigerant in said transcritical vapor cycle;
a compressor upstream of said gas cooler for compressing the refrigerant to a pressure above a critical point for the refrigerant; and
an expansion device for expanding the refrigerant downstream of said gas cooler;
wherein said evaporator heat exchanger is downstream of said expansion device, and the refrigerant passing through said gas cooler to heat said fluid to be heated is generally above the critical point;
wherein said refrigerant is CO 2 ; and
wherein there is a return line heat exchanger on said bypass line and upstream of said evaporator heat exchanger.
2. The gas turbine engine as set forth in claim 1 , wherein said fluid to be heated is air in a bypass duct.
3. The gas turbine engine as set forth in claim 1 , wherein said return line heat exchanger is cooled by ram cooling air.
4. The gas turbine engine as set forth in claim 1 , wherein said return line heat exchanger is cooled by air from an air cycle machine.
5. A gas turbine engine comprising:
a compressor section;
a combustor;
a turbine section;
a fuel supply system for supplying fuel to said combustor, said fuel supply system having a fuel delivery line for delivering fuel from a fuel tank to said combustor and there being a fuel heating heat exchanger on said fuel delivery line, and there being a bypass line for bypassing fuel downstream of said fuel heating heat exchanger back to said fuel tank;
fuel in said bypass line being a fluid to be cooled;
an associated fluid to be heated; and
a transcritical vapor cycle for heating said fluid to be heated, and for cooling said fluid to be cooled, said transcritical vapor cycle including:
a gas cooler, in which said fluid to be heated is heated by a refrigerant in said transcritical vapor cycle;
an evaporator heat exchanger at which said fluid to be cooled is cooled by the refrigerant in said transcritical vapor cycle;
a compressor upstream of said gas cooler for compressing the refrigerant to a pressure above a critical point for the refrigerant; and
an expansion device for expanding the refrigerant downstream of said gas cooler;
wherein said evaporator heat exchanger is downstream of said expansion device, and the refrigerant passing through said gas cooler to heat said fluid to be heated is generally above the critical point;
wherein said expansion device is a turbo expander;
wherein said fluid to be heated is air in a bypass duct;
wherein said refrigerant is CO 2 ; and
wherein there is a return line heat exchanger on said bypass line and upstream of said evaporator heat exchanger.
6. The gas turbine engine as set forth in claim 5 , wherein said turbo expander is configured to drive a shaft to provide drive input to said compressor.
7. The gas turbine engine as set forth in claim 6 , wherein said return line heat exchanger is cooled by ram cooling air.
8. The gas turbine engine as set forth in claim 6 , wherein said return line heat exchanger is cooled by air from an air cycle machine.
9. The gas turbine engine as set forth in claim 6 , wherein there are a plurality of said return line heat exchangers.
10. The gas turbine engine as set forth in claim 5 , wherein said return line heat exchanger is cooled by ram cooling air.
11. The gas turbine engine as set forth in claim 5 , wherein said return line heat exchanger is cooled by air from an air cycle machine.
12. The gas turbine engine as set forth in claim 5 , wherein there are a plurality of said return line heat exchangers.
13. A gas turbine engine comprising:
a compressor section;
a combustor;
a turbine section;
a fuel supply system for supplying fuel to said combustor, and including a fuel heating heat exchanger, with a bypass line downstream of said fuel heating heat exchanger for bypassing fuel back to a fuel tank;
fuel in said bypass line being a fluid to be cooled;
an associated fluid to be heated; and
a transcritical vapor cycle for heating said fluid to be heated, and for cooling said fluid to be cooled, said transcritical vapor cycle including:
a gas cooler, in which said fluid to be heated is heated by a refrigerant in said transcritical vapor cycle;
an evaporator heat exchanger at which said fluid to be cooled is cooled by the refrigerant in said transcritical vapor cycle;
a compressor upstream of said gas cooler for compressing the refrigerant to a pressure above a critical point for the refrigerant; and
an expansion device for expanding the refrigerant downstream of said gas cooler;
wherein said evaporator heat exchanger is downstream of said expansion device, and the refrigerant passing through said gas cooler to heat said fluid to be heated is generally above the critical point;
wherein said refrigerant is CO 2 ; and
wherein there is a return line heat exchanger on said bypass line and upstream of said evaporator heat exchanger.
14. The gas turbine engine as set forth in claim 13 , wherein said return line heat exchanger is cooled by ram cooling air; or
said return line heat exchanger is cooled by air from an air cycle machine.