Gas turbine engine driven by supercritical power generation system

Patent metadata

Field	Value
Publication number	US-9885283-B2
Application number	US-201514729318-A
Country	US
Kind code	B2
Filing date	Jun 3, 2015
Priority date	Jun 5, 2014
Publication date	Feb 6, 2018
Grant date	Feb 6, 2018

Abstract

A gas turbine engine includes a shaft having a first air compressor coupled thereto, a combustor positioned to receive compressed air from the first compressor, and a power source coupled to the shaft, the power source powered by a working fluid other than the compressed air.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a shaft having a first air compressor coupled thereto;
a combustor positioned to receive compressed air from the first compressor;
a power source coupled to the shaft, the power source powered by a working fluid other than the compressed air, the power source including:
a second compressor coupled to the shaft;
a turbine coupled to the shaft; and
a first closed circuit that directs a working fluid from a heat exchanger, through the second compressor, through the combustor, to the turbine, and to the heat exchanger, providing power from the turbine to the shaft; and
a second closed circuit that draws the working fluid from the heat exchanger, passes the working fluid through at least one expansion device and to at least one evaporator to receive thermal load, and to at least one third compressor that is coupled to at least one related shaft.

2. The gas turbine engine of claim 1 , wherein the first air compressor is a fan.

3. The gas turbine engine of claim 2 , further comprising a fourth compressor coupled to the shaft and positioned to receive compressed air from the fan, and pass the compressed air to the combustor.

4. The gas turbine engine of claim 1 , wherein the first closed circuit includes a recuperative heat exchanger positioned to receive the working fluid from the second compressor, and receive the working fluid from the turbine, exchanging heat therebetween.

5. The gas turbine engine of claim 1 , wherein the working fluid is carbon dioxide.

6. A method of providing power, comprising:
passing compressed air from a first compressor to a combustor, wherein the first compressor is coupled to a shaft;
providing power to the shaft using a working fluid other than the compressed air;
passing the working fluid in a closed circuit from a heat exchanger to a second compressor;
passing the working fluid from the second compressor to the combustor;
passing the working fluid from the combustor to a turbine that is coupled to the shaft;
passing the working fluid from the turbine to the heat exchanger;
drawing the working fluid from the heat exchanger;
passing the drawn working fluid through at least one expansion device and to at least one evaporator;
receiving a thermal load in the working fluid, heating the working fluid that is in said at least one evaporator; and
compressing the heated working fluid from at least one said evaporator in at least one third compressor that is coupled to at least one related shaft.

7. The method of claim 6 , wherein the first compressor is a fan.

8. The method of claim 7 , further comprising:
receiving compressed air from the fan in a fourth compressor; and
passing the compressed air from the fourth compressor to the combustor.

9. The method of claim 6 , further comprising:
receiving the working fluid from the second compressor in a recuperative heat exchanger and at a first temperature; and
receiving the working fluid from the turbine in the recuperative heat exchanger at a second temperature that is above the first temperature, increasing the temperature of the working fluid from the second compressor.

10. The method of claim 6 , wherein the working fluid is carbon dioxide.

11. A device, comprising:
a shaft having a thrust-producing device coupled thereto;
a combustor positioned to receive compressed air from the thrust-producing device;
a power circuit coupled to the shaft, the power circuit powered by carbon dioxide, the power circuit including:
a carbon dioxide compressor coupled to the shaft;
a carbon dioxide turbine coupled to the shaft; and
flow lines that direct the carbon dioxide through the carbon dioxide compressor, to the combustor, to the carbon dioxide turbine, and to a heat exchanger, providing power from the carbon dioxide turbine to the shaft; and

a cooling circuit that draws the carbon dioxide from the heat exchanger, passes the carbon dioxide through at least one expansion device and to at least one evaporator to receive thermal load, and to at least one second carbon dioxide compressor that is coupled to at least one related shaft.

12. The device of claim 11 , wherein the thrust-producing device is a fan.

13. The device of claim 12 , further comprising an air compressor coupled to the shaft and positioned to receive compressed air from the fan, and pass the compressed air to the combustor.

14. The device of claim 11 , wherein the power circuit includes a recuperative heat exchanger positioned to receive the carbon dioxide from the carbon dioxide compressor, and receive the carbon dioxide from the turbine, exchanging heat therebetween.

Assignees

• Rolls Royce Corp

Inventors

• Vaisman Igor
• Bastnagel Thomas E

Classifications

• F05D2210/20

  Properties · CPC title

• F02K3/06 Primary

  with front fan · CPC title

• F25B9/06

  using expanders (F25B9/10 takes precedence) · CPC title

• F25B2327/00

  Compressor driving means · CPC title

• F05D2210/10

  Kind or type · CPC title