UTILIZING HEAT DISCARDED FROM A GAS TURBINE ENGINE

• US 20120096869A1
• Filed: 10/26/2011
• Published: 04/26/2012
• Est. Priority Date: 10/26/2010
• Status: Abandoned Application

• Current Assignee: ICR Turbine Engine Corporation
• Original Assignee: ICR Turbine Engine Corporation
• Inventors: Kesseli, James B., Watson, John D., Vandervalk, William
• Application Number:
  US13/281,702
• Publication Number:
  US 20120096869A1
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: F02C 3/20 using a special fuel, oxidant, or dilution fluid to generate the combustion products
• CPC Class Codes: F02C 7/10 by means of regenerative heat-exchangers
• CPC Class Codes: F02C 7/143 before or between the compressor stages
• CPC Class Codes: F02C 7/224 Heating fuel before feeding to the burner
• CPC Class Codes: Y02E 50/10 Biofuels, e.g. bio-diesel
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Various embodiments are disclosed to utilize various fuels, including liquid natural gas fuels, to improve engine efficiency in gas turbine engines. In one configuration, a fuel is heated by a heat exchanger utilizing waste exhaust heat of a gas turbine engine. In another configuration, LNG fuel is heated using a pre-cooler for the inlet air stream of a gas turbine engine. In another configuration, fuel is injected into the pressurized air, downstream of the air-to-air intercooler. In yet another configuration, fuel is pumped through the engine'"'"'s intercooler or a secondary heat exchanger exchanging heat with the compressed air stream between the low-pressure compressor and high-pressure compressor. In another configuration, the fuel is first heated by the intercooler and then further heated by a heat exchanger utilizing waste exhaust heat of the gas turbine engine.

Claims

1. An apparatus, comprising:

one or more turbo-compressor spools in fluid communication with one another, each of the one or more turbo-compressor spools comprising a compressor in mechanical communication with a turbine;

a fuel source comprising a fuel;

one of a heat exchanger and heat jacket to transfer heat from a fluid associated with operation of the one or more turbo-compressor spools to a portion of the fuel to substantially heat the portion of the fuel to form a heated fuel; and

a combustor operable to combust the heated fuel.

2. The apparatus of claim 1, wherein the one of a heat exchanger and heat jacket transfers heat from a working fluid exiting the one or more turbo-compressor spools, to the portion of the fuel.

3. The apparatus of claim 1, wherein the one of a heat exchanger and heat jacket transfers heat from a working fluid exiting a recuperator downstream of a free power turbine;

to the portion of the fuel.

4. The apparatus of claim 1, wherein the one of a heat exchanger and heat jacket transfers heat from a working fluid entering the engine inlet duct, to the portion of the fuel.

5. The apparatus of claim 2, wherein the one of a heat exchanger and heat jacket is an intercooler positioned in a fluid path between any two of the one or more turbo-compressor spools.

6. The apparatus of claim 3, wherein the one of a heat exchanger and heat jacket is in thermal contact with the working fluid passing through the engine exhaust pipe.

7. The apparatus of claim 4, wherein the one of a heat exchanger and heat jacket is in thermal contact with the working fluid passing through the engine inlet duct.

8. The apparatus of claim 1, wherein the heat exchanger is a recuperator, wherein the working fluid is an output gas of a free power turbine.

9. The apparatus of claim 1, wherein the one of a heat exchanger and heat jacket is positioned in a fluid path between the compressors in first and second turbo-compressor spools.

10. The apparatus of claim 1, wherein the one of a heat exchanger and heat jacket is positioned in a fluid path between the turbines in first and second turbo-compressor spools.

11. The apparatus of claim 1, wherein the one of a heat exchanger and heat jacket is positioned in a fluid path between the turbine in the first turbo-compressor spool and a free power turbine.

12. The apparatus of claim 1, wherein the one of a heat exchanger and heat jacket is positioned in a fluid path between a compressor and turbine of the second turbo-compressor spool.

13. The apparatus of claim 1, wherein the fuel provided by the fuel source is at least one of liquid natural gas, liquid natural gas vapor, gaseous methane, diesel, kerosene, gasoline, bio-diesel, ethanol, methanol, butanol, ammonia, and hydrogen.

14. The apparatus of claim 1, wherein the one of a heat exchanger and heat jacket transfers to the fuel portion heat from at least one of an engine inlet duct, the one or more turbo-compressor spools and an engine exhaust pipe.

23. The method of claim 12, wherein the fuel is LNG and the LNG is substantially vaporized by introduction of the LNG into the first working fluid downstream of an intercooler and upstream of the compressor in the second turbo-compressor spool.

15. A method, comprising:

compressing, by a compressor in a first turbo-compressor spool, an inlet gas to form a first working fluid;

compressing, by a compressor in a second turbo-compressor spool, the first working fluid to form a second working fluid;

substantially heating a fuel comprising at least one of liquid natural gas, liquid natural gas vapor, gaseous methane, diesel, kerosene, gasoline, bio-diesel, methanol, ethanol, butanol, ammonia, and hydrogen to form a heated gas;

combusting the fuel and the second working fluid to form a combusted working fluid;

driving, by the combusted working fluid, a turbine of the second turbo-compressor spool; and

driving, by the combusted working fluid, a turbine of the first turbo-compressor spool.

16. The method of claim 15, wherein the fuel is substantially heated by one of a heat exchanger and heat jacket, the one of a heat exchanger and heat jacket transferring heat from at least one of the inlet gas, the first working fluid, the second working fluid and the combusted working fluid.

17. The method of claim 15, wherein the fuel is substantially heated by heat transferred from the combusted working fluid after the combusted working fluid has exited a free power turbine.

18. The method of claim 15, wherein the fuel is substantially heated by heat transferred from the combusted working fluid after the combusted working fluid has exited a recuperator.

19. The method of claim 15, wherein the fuel is substantially heated by one of a heat exchanger and heat jacket, the one of a heat exchanger and heat jacket transferring heat from an inlet gas to the compressor in the first turbo-compressor spool.

20. The method of claim 16, wherein the heat exchanger is an intercooler positioned in a fluid path between the first and second turbo-compressor spools.

21. The method of claim 16, wherein the one of a heat exchanger and heat jacket is in thermal contact with the working fluid passing through an engine exhaust pipe.

22. The method of claim 16, wherein the one of a heat exchanger and heat jacket is in thermal contact with the working fluid passing through an engine inlet duct.

24. An apparatus, comprising:

at least first and second turbo-compressor spools in fluid communication with one another, each of the at least first and second turbo-compressor spools comprising a compressor in mechanical communication with a turbine;

a fuel source comprising at least one of liquid natural gas, liquid natural gas vapor, gaseous methane, diesel, kerosene, gasoline, bio-diesel, methanol, ethanol, butanol, ammonia, and hydrogen;

a fuel path to introduce fuel into a working fluid path to substantially heat the fuel to form a gas; and

a combustor operable to combust the gas.

25. The apparatus of claim 24, wherein a section of the working fluid path is positioned between a compressor of the first turbo-compressor spool and a compressor of the second turbo-compressor spool and wherein the fuel fluid path fluidly connects with the working fluid path.

26. The apparatus of claim 25 wherein the fuel is LNG at a temperature where the LNG is a liquid.

27. The apparatus of claim 24, wherein a section of the working fluid path is positioned between a compressor of the second turbo-compressor spool and a turbine of the second turbo-compressor spool and wherein the fuel fluid path fluidly connects with the working fluid path and wherein the fuel is contacted with the working fluid upstream of the combustor.

28. The apparatus of claim 25 wherein the fuel is LNG at a temperature where the LNG is a liquid and wherein the fuel is vaporized when contacted with the working fluid.