Additive injection system for improving thermal stability of jet fuel

• US 8,234,870 B2
• Filed: 04/17/2009
• Issued: 08/07/2012
• Est. Priority Date: 04/17/2009
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Gage, Marc E.
• Primary Examiner(s): Rodriguez, William H
• Assistant Examiner(s): Rivera, Carlos A
• Application Number:
  US12/386,397
• Publication Number:
  US 20100263348A1
• Time in Patent Office: 1,208 Days
• Field of Search: 607/34, 607/36, 607/76, 60/392.81, 244/135.A
• US Class Current: 60/734
• CPC Class Codes: F02C 3/305 Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids F01K21/04 takes precedence
• CPC Class Codes: G05D 11/006 involving a first fluid acting on the feeding of a second fluid
• CPC Class Codes: Y10T 137/2499 Mixture condition maintaining or sensing

Abstract

A gas turbine engine fuel system includes a fuel tank for storing fuel, a heat exchanger through which the fuel from the fuel tank can pass, a fuel pump located downstream from the heat exchanger for pumping the fuel, a fuel metering unit for metering the fuel pumped by the fuel pump, an additive tank for storing a fuel additive, an additive delivery subsystem for mixing the fuel additive with the fuel at or before the heat exchanger to generate a fuel and fuel additive mixture, and a combustor located downstream of the fuel metering unit where the fuel and fuel additive mixture is delivered for combustion. The fuel additive comprises a fuel stabilizer for reducing fuel coking.

Claims

1. A gas turbine engine fuel system comprising:

a fuel tank on an aircraft for storing fuel;

a heat exchanger through which the fuel from the fuel tank can pass;

a fuel pump located downstream from the heat exchanger for pumping the fuel;

a fuel metering unit for metering the fuel pumped by the fuel pump;

an additive tank on the aircraft for storing a fuel additive, wherein the fuel additive comprises a fuel stabilizer for reducing fuel coking;

an additive delivery subsystem for mixing the fuel additive with the fuel at or before the heat exchanger at a location on the aircraft downstream from the fuel tank to generate a fuel and fuel additive mixture; and

a combustor located downstream of the fuel metering unit where the fuel and fuel additive mixture is delivered for combustion.

2. The system of claim 1 and further comprising:

a first recirculation line for recirculating at least a portion of the fuel and fuel additive mixture to a location upstream of the fuel pump; and

a second recirculation line for recirculating at least a portion of the fuel additive to an upstream location.

3. The system of claim 1, wherein the additive delivery subsystem comprises a venturi.

4. The system of claim 1, wherein the additive delivery subsystem comprises a positive displacement additive pump.

5. The system of claim 4, wherein a drive shaft is operably connected between the positive displacement additive pump and the fuel pump such that the positive displacement additive pump and the fuel pump are rotationally driven together.

6. The system of claim 4, wherein the positive displacement additive pump is electrically driven.

7. The system of claim 1, wherein the fuel additive comprises a fuel stabilizer that reduces coking to allow an operating temperature of the fuel and fuel additive mixture of at least about 135°

C. (275°

F.).

8. The system of claim 1, wherein the fuel additive comprises a fuel stabilizer that increases an operating temperature of fuel and fuel additive mixture over an operating temperature of the fuel by at least about 38°

C. (100°

F.).

9. The system of claim 1, wherein the fuel is selected from the group consisting of JP-8, Jet A and Jet A-1.

20. The system of claim 1, wherein the fuel additive comprises a fuel stabilizer that reduces coking to allow an operating temperature of the fuel and fuel additive mixture of at least about 135°

C. (275°

F.).

10. A method of fuel delivery for a gas turbine engine, the method comprising:

providing jet fuel on an aircraft;

transferring thermal energy to the jet fuel from oil using a fuel/oil heat exchanger;

pumping the jet fuel toward a combustor using a fuel pump;

metering the jet fuel downstream of the fuel pump to control a jet fuel delivery rate;

providing a fuel additive on the aircraft that comprises a fuel stabilizer to reduce fuel coking at elevated operating temperatures;

mixing the fuel additive to the jet fuel at or before the heat exchanger at a location on the aircraft downstream from a jet fuel storage tank; and

delivering a mixture of the fuel additive and the jet fuel to the combustor.

11. The method of claim 10, wherein the jet fuel is pumped with a first positive displacement pump, wherein the fuel additive is pumped with a second positive displacement pump, and wherein a common rotational input drives both the first and second positive displacement pumps.

12. The method of claim 10, wherein the fuel additive is pumped with a positive displacement pump, the method further comprising:

providing electricity to power the positive displacement pump.

13. The method of claim 10 and further comprising:

recirculating at least a portion of the fuel additive to control a ratio of the fuel additive to the jet fuel;

recirculating at least a portion of the mixture of the fuel additive and the jet fuel to control dosage.

14. An aircraft fuel system comprising:

a fuel tank on the aircraft for storing fuel;

a fuel/oil heat exchanger through which the fuel from the fuel tank can pass, wherein the fuel/oil heat exchanger is configured to transfer thermal energy from oil to the fuel;

a positive displacement fuel pump located downstream from the heat exchanger for pumping the fuel;

a fuel metering unit for metering the fuel pumped by the fuel pump;

an additive tank on the aircraft for storing a fuel additive, wherein the fuel additive comprises a fuel stabilizer for reducing fuel coking at elevated operating temperatures;

an additive delivery subsystem for mixing the fuel additive with the fuel at or before the heat exchanger and downstream from the fuel tank to generate a fuel and fuel additive mixture; and

a combustor located downstream of the fuel metering unit where the fuel and fuel additive mixture is delivered for combustion.

15. The system of claim 14 and further comprising:

a first recirculation line for recirculating at least a portion of the fuel and fuel additive mixture to a location upstream of the positive displacement fuel pump; and

a second recirculation line for recirculating at least a portion of the fuel additive to an upstream location.

16. The system of claim 14, wherein the additive delivery subsystem comprises a venturi.

17. The system of claim 14, wherein the additive delivery subsystem comprises a positive displacement additive pump.

18. The system of claim 17, wherein a drive shaft is operably connected between the positive displacement additive pump and the positive displacement fuel pump such that the positive displacement additive pump and the positive displacement fuel pump are rotationally driven together.

19. The system of claim 17, wherein the positive displacement additive pump is electrically driven.