HIGH PRESSURE RATIO TWIN SPOOL INDUSTRIAL GAS TURBINE ENGINE

• US 20160215694A1
• Filed: 09/11/2014
• Published: 07/28/2016
• Est. Priority Date: 07/22/2013
• Status: Abandoned Application

• Current Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: BROSTMEYER, Joseph D., CEJKA, Justin T., JONES, Russell B.
• Application Number:
  US15/021,531
• Publication Number:
  US 20160215694A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F01K 23/10 with exhaust fluid of one cycle heating the fluid in another cycle F01K17/025 takes precedence
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02C 3/34 with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
• CPC Class Codes: F02C 7/143 before or between the compressor stages
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: H02K 7/1823 structurally associated with turbines or similar engines
• CPC Class Codes: Y02E 20/16 Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, where the low pressure spool is operated at high electrical demand to supply compressed air to the high pressure compressor of the high pressure spool, and where turbine exhaust is used to drive a second electric generator from steam produced in a heat recovery steam generator. The power plant can operate at 25% of peak load while keeping the unused parts of the power plant hot for easy restart when high power output is required.

Claims

1-16. -16. (canceled)

17. An industrial gas turbine engine for electrical power production, the industrial gas turbine engine comprising:

a high pressure spool with a high pressure compressor driven by a high pressure turbine;

a combustor operable between the high pressure compressor and the high pressure turbine;

an electric generator directly coupled to the high pressure spool in synchronous operation with a local area power grid;

a low pressure spool with a low pressure compressor driven by a low pressure turbine, the high pressure spool and the low pressure spool being rotatably independent, the low pressure compressor being connected to the high pressure compressor to supply compressed air from the low pressure compressor to the high pressure compressor;

a first row of variable inlet guide vanes on the high pressure compressor;

a second row of variable inlet guide vanes on the low pressure turbine; and

a third row of variable inlet guide vanes on the low pressure compressor.

18. The industrial gas turbine engine for electric power production of claim 17, and further comprising:

an intercooler to cool the compressed air from the low pressure compressor to the high pressure compressor.

19. The industrial gas turbine engine for electric power production of claim 17, and further comprising:

a boost compressor connected to the low pressure compressor, the boost compressor being connected to an airfoil cooling circuit of the high pressure turbine;

the airfoil cooling circuit of the high pressure turbine airfoil being connected to an inlet of the combustor; and

compressed air from the low pressure compressor being further compressed such that cooling air flows through the airfoil cooling circuit and then into the combustor.

20. The industrial gas turbine engine for electric power production of claim 19, and further comprising:

an intercooler located between the low pressure compressor and the boost compressor to provide cooling of the compressed air.

21. The industrial gas turbine engine for electric power production of claim 17, and further comprising:

a heat recovery steam generator connected to an exhaust of the industrial gas turbine engine; and

a second electric generator connected to the heat recovery steam generator.

22. The industrial gas turbine engine for electric power production of claim 19, and further comprising:

a diffuser on an outlet side of the high pressure compressor, the diffuser having an inlet for compressed air from the high pressure compressor and an inlet for the cooling air from the turbine airfoil cooling circuit with the cooling air being injected parallel to the compressed air from the high pressure compressor.

35. The industrial gas turbine engine for electric power production of claim 17, wherein the industrial gas turbine engine is a 50 hertz engine with a power output of at least 750 MW.

36. The industrial gas turbine engine for electric power production of claim 17, wherein the industrial gas turbine engine is a 60 hertz engine with a power output of at least 500 MW.

23. An industrial gas turbine engine for electrical power production, the industrial gas turbine engine comprising:

a high pressure spool with a high pressure compressor driven by a high pressure turbine;

a combustor operable between the high pressure compressor and the high pressure turbine;

an electric generator directly coupled to the high pressure spool in synchronous operation with a local area power grid;

a low pressure spool with a low pressure compressor driven by a low pressure turbine, the high pressure spool and the low pressure spool being rotatably independent, the low pressure compressor being connected to the high pressure compressor to supply compressed air to the high pressure compressor;

a row of variable inlet guide vanes on the low pressure turbine; and

an intercooler to cool the compressed air from the low pressure compressor.

24. The industrial gas turbine engine for electric power production of claim 23, and further comprising:

an intercooler located between the low pressure compressor and the boost compressor to provide cooling of the compressed air.

25. The industrial gas turbine engine for electric power production of claim 23, and further comprising:

a second row of variable inlet guide vanes on the low pressure turbine; and

a third row of variable inlet guide vanes on the high pressure compressor.

26. The industrial gas turbine engine for electric power production of claim 23, and further comprising:

a boost compressor connected to the low pressure compressor, the boost compressor being connected to a turbine airfoil cooling circuit of the high pressure turbine, the turbine airfoil cooling circuit of the high pressure turbine airfoil being connected to an inlet of the combustor; and

compressed air from the low pressure compressor being further compressed such that cooling air flows through the turbine airfoil cooling circuit and then into the combustor.

27. The industrial gas turbine engine for electric power production of claim 23, and further comprising:

a heat recovery steam generator connected to an exhaust of the industrial gas turbine engine; and

a second electric generator connected to the heat recovery steam generator.

28. The industrial gas turbine engine for electric power production of claim 23, and further comprising:

a diffuser on an outlet side of the high pressure compressor, the diffuser having an inlet for compressed air from the high pressure compressor and an inlet for the cooling air from the turbine airfoil cooling circuit with the cooling air being injected parallel to the compressed air from the high pressure compressor.

29. An industrial gas turbine engine for electrical power production, the industrial gas turbine engine comprising:

a high pressure spool with a high pressure compressor driven by a high pressure turbine;

an intermediate pressure turbine connected immediately downstream from the high pressure turbine and connected to a synchronous operating electric generator by an intermediate rotor shaft;

a low pressure spool with a low pressure compressor driven by a low pressure turbine, the low pressure turbine being driven by exhaust from the intermediate pressure turbine, the high pressure spool and the low pressure spool being rotatably independent, and the intermediate rotor shaft being concentric to and rotating within the low pressure spool;

an outlet of the low pressure compressor connected to an inlet of the high pressure compressor to supply compressed air to the high pressure compressor;

an intercooler to cool the compressed air from the low pressure compressor to the high pressure compressor; and

a row of variable inlet guide vanes in the low pressure turbine.

30. The industrial gas turbine engine for electric power production of claim 29, and further comprising:

a second row of variable inlet guide vanes in the high pressure compressor; and

a third row of variable inlet guide vanes in the low pressure compressor.

31. The industrial gas turbine engine for electric power production of claim 29, and further comprising:

a boost compressor connected to the outlet of the intercooler; and

an outlet of the boost compressor connected to a turbine airfoil cooling circuit of the high pressure turbine, the turbine airfoil cooling circuit of the high pressure turbine airfoil being connected to an inlet of the combustor, and compressed air from the low pressure compressor being further compressed such that cooling air flows through the turbine airfoil cooling circuit and then into the combustor.

32. The industrial gas turbine engine for electric power production of claim 31, and further comprising:

an intercooler located between the low pressure compressor and the boost compressor to provide cooling of the compressed air.

33. The industrial gas turbine engine for electric power production of claim 29, and further comprising:

a heat recovery steam generator connected to an exhaust of the industrial gas turbine engine; and

a second electric generator connected to the heat recovery steam generator.

34. The industrial gas turbine engine for electric power production of claim 29, and further comprising:

a diffuser on an outlet side of the high pressure compressor, the diffuser having an inlet for compressed air from the high pressure compressor and an inlet for the cooling air from the turbine airfoil cooling circuit with the cooling air being injected parallel to the compressed air from the high pressure compressor.

37. An industrial gas turbine engine for electrical power production, the industrial gas turbine engine comprising:

a high pressure spool with a high pressure compressor driven by a high pressure turbine;

a combustor operable between the high pressure compressor and the high pressure turbine;

an electric generator directly coupled to the high pressure spool in synchronous operation with a local area power grid;

a low pressure spool with a low pressure compressor driven by a low pressure turbine, the high pressure spool and the low pressure spool being rotatably independent;

a row of variable inlet guide vanes in the low pressure turbine;

a compressed air line fluidly connecting the low pressure compressor to the high pressure compressor to supply compressed air from the low pressure compressor to the high pressure compressor;

a stator vane cooling circuit connected to the compressed air line downstream from the intercooler and passing through a row of stator vanes in the high pressure turbine;

a rotor blade cooling circuit connected to the compressed air line downstream from the intercooler and passing through a row of rotor blades in the high pressure turbine;

a boost compressor located between the low pressure compressor and the stator vane cooling circuit and the rotor blade cooling circuit; and

a diffuser located between an outlet of the high pressure compressor and an inlet of the combustor, the diffuser having an inner plenum and an outer plenum separated by a compressed air passage from the outlet of the high pressure compressor, the stator vane cooling circuit discharges into the outer plenum, the rotor blade cooling circuit discharges into the inner plenum, and cooling air from the inner plenum and the outer plenum flowing substantially parallel to the compressed air from the high pressure compressor into the combustor.

38. The industrial gas turbine engine for electric power production of claim 37, and further comprising:

a second row of variable inlet guide vanes in the high pressure compressor; and

a third row of variable inlet guide vanes in the low pressure compressor.

39. The industrial gas turbine engine for electric power production of claim 37, and further comprising:

an intercooler located between the low pressure compressor and the boost compressor to cool the compressed air.

40. An industrial gas turbine engine for electrical power production, the industrial gas turbine engine comprising:

a main spool with a high pressure compressor driven by a high pressure turbine;

a combustor operable between the high pressure compressor and the high pressure turbine;

an electric generator directly coupled to the main spool and configured to be in synchronous operation with a local area power grid;

a turbocharger spool with a low pressure compressor driven by a low pressure turbine, the low pressure compressor connected to the high pressure compressor to supply compressed air to the high pressure compressor;

a first row of variable inlet guide vanes on the high pressure compressor;

a second row of variable inlet guide vanes on the low pressure turbine; and

a third row of variable inlet guide vanes on the low pressure compressor.

41. The industrial gas turbine engine for electric power production of claim 40, wherein the main spool and the turbocharger spool are capable of operating at speeds independent of one another.