Gas turbine engine system with bleed air powered auxiliary engine

Patent metadata

Field	Value
Publication number	US-9297304-B2
Application number	US-98244910-A
Country	US
Kind code	B2
Filing date	Dec 30, 2010
Priority date	Dec 30, 2009
Publication date	Mar 29, 2016
Grant date	Mar 29, 2016

Abstract

One embodiment of the present invention is a unique gas turbine engine with a bleed air powered auxiliary engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for bleed air powered auxiliary engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

First claim

What is claimed is:

1. A gas turbine engine system, comprising:
a compressor forming a source of pressurized air;
a first combustor in fluid communication with said compressor and configured to receive working fluid consisting of pressurized air directly from the compressor prior to the working fluid passing through a heat addition component or an expansion component;
a second combustor in fluid communication with said compressor in parallel with said first combustor and configured to receive working fluid consisting of pressurized air directly from the compressor prior to the working fluid passing through a heat addition component or an expansion component;
a first turbine in fluid communication with and downstream of said first combustor;
a second turbine in fluid communication with said second combustor; and
a third turbine in fluid communication with said second combustor, wherein said third turbine is on a different spool than said second turbine;
wherein the second combustor, the second turbine, and the third turbine are configured as an auxiliary engine, wherein the auxiliary engine does not include a compressor.

2. The gas turbine engine system of claim 1 , further comprising a bleed system in fluid communication with said compressor, wherein said second combustor is in fluid communication with said compressor via said bleed system.

3. The gas turbine engine system of claim 1 , further comprising a duct fluidly coupling said second combustor with said compressor.

4. The gas turbine engine system of claim 1 , further comprising a reduction gearbox coupled to said second turbine.

5. The gas turbine engine system of claim 1 , wherein said third turbine is downstream of said second turbine.

6. The gas turbine engine system of claim 1 , further comprising a gearbox coupled to both said second turbine and said third turbine, wherein said gearbox is structured to maintain a constant speed ratio between said second turbine and said third turbine.

7. The gas turbine engine system of claim 1 , further comprising a reduction gearbox coupled to at least one of said second turbine and said third turbine.

8. The gas turbine engine system of claim 7 , wherein said reduction gearbox is coupled to both said second turbine and said third turbine.

9. The gas turbine engine system of claim 1 , further comprising a valve structured to control the flow of bleed air into said second combustor.

10. The gas turbine engine system of claim 9 , wherein said valve is a fast-acting air valve.

11. A turbine system configured to operate using pressurized air from a pressurized bleed air source associated with another turbine engine system, comprising:
a combustor in fluid communication with the pressurized bleed air source and configured to receive working fluid consisting of the pressurized air directly from the pressurized bleed air source prior to the working fluid passing through a heat addition component or an expansion component;
a valve disposed between the pressurized bleed air source and the combustor, wherein the valve is configured to control a flow of pressurized air from the pressurized bleed air source into the combustor;
a first turbine in fluid communication with the combustor;
a second turbine in fluid communication with the first turbine;
a primary combustor in fluid communication with the pressurized bleed air source in parallel with the combustor, the primary combustor configured to receive working fluid consisting of pressurized air directly from the pressurized bleed source prior to the working fluid passing through a heat addition component or an expansion component; and
a primary turbine in fluid communication with the primary combustor and directly downstream of the primary combustor;
wherein the combustor, the first turbine, and the second turbine are configured as an auxiliary engine, wherein the auxiliary engine does not include a compressor.

12. The turbine engine system of claim 11 , wherein the pressurized bleed air source is a compressor bleed from a compressor of a gas turbine engine.

13. The turbine engine system of claim 11 , further comprising a gearbox coupled to both the first turbine and the second turbine, wherein the gearbox is structured to control a speed ratio between the first turbine and the second turbine.

14. The turbine engine system of claim 11 , wherein the first turbine and the second turbine are configured to supply power to a machine.

15. The turbine engine system of claim 11 , further comprising a reduction gearbox is coupled to both the first turbine and the second turbine.

16. The turbine engine system of claim 11 , wherein at least one of the first and second turbines are connected to an electrical generator configured to supply power to a machine.

17. The gas turbine engine system of claim 1 , wherein power generation components of the auxiliary engine consist of the second combustor, the second turbine, and the third turbine.

18. The gas turbine engine system of claim 11 , wherein power generation components of the auxiliary engine consist of the combustor, the first turbine, and the second turbine.

Assignees

• Nordstrom Carl David
• Bowman Ray F
• Rolls Royce Nam Tech Inc

Inventors

• Nordstrom Carl David
• Bowman Ray F

Classifications

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F02C3/14

  characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) · CPC title

• F02C3/10 Primary

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