Cryogenic fuel system and method for delivering fuel in an aircraft

Patent metadata

Field	Value
Publication number	US-9932124-B2
Application number	US-201314654925-A
Country	US
Kind code	B2
Filing date	Nov 26, 2013
Priority date	Dec 28, 2012
Publication date	Apr 3, 2018
Grant date	Apr 3, 2018

Abstract

A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine.

First claim

What is claimed is:

1. A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, comprising:
a cryogenic fuel stored in a tank;
a supply line operably coupling the tank to the combustion chamber;
a first pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump; and
a second pump fluidly coupling the tank to the first pump to pre-pressurize the cryogenic fuel delivered to the first pump.

2. The cryogenic fuel system of claim 1 , wherein the first pump pressurizes the cryogenic fuel to a pressure higher than the pressure of air coming into the combustion chamber of the turbine engine from the compressor section of the turbine engine.

3. The cryogenic fuel system of claim 2 , wherein the cryogenic fuel is Liquefied Natural Gas (LNG).

4. The cryogenic fuel system of claim 1 , wherein the first pump is a turbopump having a turbine section and a centrifugal pump section.

5. The cryogenic fuel system of claim 4 , wherein the cryogenic fuel is Liquefied Natural Gas (LNG).

6. The cryogenic fuel system of claim 4 , wherein the turbine section of the turbopump is fluidly coupled to the compressor to discharge pressure from the turbine engine such that the discharge pressure from the compressor drives the first pump.

7. The cryogenic fuel system of claim 6 , wherein the turbine section of the turbopump effects rotation of the centrifugal pump section of the turbopump to pressurize the cryogenic fuel in the cryogenic fuel system.

8. The cryogenic fuel system of claim 7 , further comprising an air valve fluidly coupled between the compressor section of the turbine engine and the turbine section of the turbopump and where the air valve is configured to modulate a flow of air to discharge pressure from the compressor to the turbine section of the turbopump.

9. The cryogenic fuel system of claim 8 , further comprising a charge pump fluidly coupling the tank to the centrifugal pump section of the turbopump to increase pressure of the cryogenic fuel delivered to the centrifugal pump section of the turbopump.

10. The cryogenic fuel system of claim 1 , wherein the first pump is a turbopump having a turbine section and a pump section having a pump type selected from one of: a reciprocating pump, a screw pump, a vane pump, or a gear pump.

11. The cryogenic fuel system of claim 10 , wherein the cryogenic fuel is Liquefied Natural Gas (LNG).

12. The cryogenic fuel system of claim 1 , wherein the cryogenic fuel is Liquefied Natural Gas (LNG).

13. A method for delivering cryogenic fuel in a fuel system to a turbine engine having a combustion section and a compressor section, comprising:
pressurizing the cryogenic fuel provided to the combustion section of the turbine engine utilizing a turbopump driven by the compressor to discharge pressure from the turbine engine, and
pressurizing the cryogenic fuel with a second fuel pump before said cryogenic fuel is pressurized by the turbopump.

14. The method of claim 13 , wherein the cryogenic fuel provided to the combustion section is pressurized by the turbopump to a pressure higher than the pressure of air coming into the combustion section of the turbine engine from the compressor section of the turbine engine.

15. The method of claim 14 , further comprising modulating the flow of the compressor discharge from the turbine engine to the turbopump.

16. The method of claim 13 , further comprising pre-pressurizing the cryogenic fuel prior to the cryogenic fuel being pressurized by the turbopump.

17. The method of claim 16 , further comprising modulating the flow of the compressor discharge from the turbine engine to the turbopump.

18. The method of claim 13 , further comprising modulating the flow of the compressor discharge from the turbine engine to the turbopump.

19. The method of claim 13 , further comprising modulating the flow of the compressor discharge from the turbine engine to the turbopump.

Assignees

• Gen Electric

Inventors

• Kamath Deepak Manohar
• Buchholz Todd James
• Baladi Mehdi Milani
• Epstein Michael Jay

Classifications

• F02C6/08

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

• F02C3/22 Primary

  the fuel or oxidant being gaseous at standard temperature and pressure (F02C3/28 takes precedence) · CPC title

• F02C7/224

  Heating fuel before feeding to the burner · CPC title

• F02C7/236

  Fuel delivery systems comprising two or more pumps · CPC title

• B64D37/30 Primary

  Fuel systems for specific fuels · CPC title