Engine driven by SC02 cycle with independent shafts for combustion cycle elements and propulsion elements

Patent metadata

Field	Value
Publication number	US-9982629-B2
Application number	US-201615185498-A
Country	US
Kind code	B2
Filing date	Jun 17, 2016
Priority date	Jun 19, 2015
Publication date	May 29, 2018
Grant date	May 29, 2018

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.

First claim

What is claimed is:

1. 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.

2. The gas turbine engine of claim 1 , wherein the closed-loop system includes carbon dioxide as a working fluid.

3. The gas turbine engine of claim 1 , further comprising a gear coupled to the third shaft that reduces a rotation of a fan blade within the fan assembly relative to a rotational speed of the third shaft.

4. The gas turbine engine of claim 1 , further comprising an inner housing that houses at least a portion of the first, second, and third shafts, and passes air therethrough from the fan assembly to the combustor, and the bypass air passes from the fan assembly and the bypass air passing externally to the inner housing to provide cooling to the heat rejection heat exchanger.

5. The gas turbine engine of claim 1 , wherein thrust is provided from both combustion byproducts from the combustor and from the bypass air.

6. The gas turbine engine of claim 1 , further comprising a fourth shaft having a fourth turbine and a second fan assembly coupled thereto, and a baffle positioned between the inner housing and an outer surface of the gas turbine engine, wherein:
the closed-loop system includes the fourth turbine; and
the second fan assembly provides:
bypass air as thrust air that passes between the baffle and the inner housing; and cooling air.

7. The gas turbine engine of claim 1 , the closed loop further comprising a recuperative heat exchanger that exchanges heat from the working fluid between an outlet of the first turbine and an input to the combustor.

8. 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.

9. The method of claim 8 , wherein the closed-loop system includes carbon dioxide as a working fluid.

10. The method of claim 8 , further comprising operating the first, the second, and the third shafts separately and at different speeds from one another.

11. The method of claim 8 , further comprising a gear coupled to the third shaft that reduces a rotation of a fan blade within the fan assembly relative to a rotational speed of the third shaft.

12. The method of claim 8 , further comprising passing air through an inner housing that houses at least a portion of the first, second, and third shafts, and from the fan assembly to the combustor, and passing the bypass air from the fan assembly and the bypass air that passes externally to the inner housing to provide cooling to the heat rejection heat exchanger.

13. The method of claim 8 , further comprising providing thrust from both combustion byproducts from the combustor and from the bypass air.

14. The method of claim 8 , wherein the gas turbine further comprises a fourth shaft having a fourth turbine and a second fan assembly coupled thereto, and a baffle positioned between the inner housing and an outer surface of the gas turbine engine, and the closed-loop system includes the fourth turbine;
the method further comprising providing the bypass air via the second fan assembly and as thrust air that passes between the baffle and the inner housing.

15. The method of claim 8 , the closed loop system further comprising a recuperative heat exchanger, further comprising exchanging heat from the working fluid between an outlet of the first turbine and an input to the combustor.

16. 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.

17. The power-producing device of claim 16 , wherein the closed-loop system includes carbon dioxide as a working fluid.

18. The power-producing device of claim 16 , wherein the first, the second, and the third shafts are separately operable at different speeds from one another.

19. The power-producing device of claim 16 , further comprising an inner housing that houses at least a portion of the first, second, and third shafts, and passes air therethrough from the fan assembly to the combustor, and the bypass air passes from the fan assembly and the bypass air passing externally to the inner housing to provide cooling to the heat rejection heat exchanger.

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Armstrong Michael J
• Vaisman Igor

Classifications

• F02C6/206

  the vehicles being airscrew driven · CPC title

• F02C7/141

  of working fluid · CPC title

• F05D2250/311

  the axes being in line · CPC title

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title

• F02C7/08

  Heating air supply before combustion, e.g. by exhaust gases · CPC title