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WO1998051917A1 - Method and apparatus for cooling a turbine with compressed cooling air from an auxiliary compressor system - Google Patents

Method and apparatus for cooling a turbine with compressed cooling air from an auxiliary compressor system Download PDF

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Publication number
WO1998051917A1
WO1998051917A1 PCT/US1998/008628 US9808628W WO9851917A1 WO 1998051917 A1 WO1998051917 A1 WO 1998051917A1 US 9808628 W US9808628 W US 9808628W WO 9851917 A1 WO9851917 A1 WO 9851917A1
Authority
WO
WIPO (PCT)
Prior art keywords
air stream
auxiliary
rotating shaft
compressed
compressor
Prior art date
Application number
PCT/US1998/008628
Other languages
French (fr)
Inventor
Michael Scot Briesch
Jorge J. Alba
Brian Bohinsky
Original Assignee
Siemens Westinghouse Power Corporation
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Westinghouse Power Corporation filed Critical Siemens Westinghouse Power Corporation
Publication of WO1998051917A1 publication Critical patent/WO1998051917A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas

Definitions

  • the present invention relates to providing compressed cooling air to turbines in combustion turbine systems.
  • a turbine 1 6 in a combustion turbine system 1 0 is cooled by a compressed cooling air stream 36 from a compressor 1 2 of the system.
  • the combustion turbine system 10 is comprised of the compressor 1 2, a combustor 14 and the turbine 1 6 that are operationally connected.
  • the compressor 1 2 receives an air flow 24 and compresses it to produce a first compressed air stream 26 and a second compressed air stream 34.
  • the first compressed air stream 26 is directed, along with a fuel stream 28, into the combustor 1 4.
  • the streams are combusted in the combustor 1 4 to produce a combustion emission stream 30.
  • the combustion emission stream 30 is directed to the turbine 1 6, which expands the stream 30, thereby producing expanded emissions 32 and rotating a shaft 1 8.
  • the rotating shaft 1 8 provides rotating shaft power to the compressor 1 2 for its operation and to the generator 22 which produces electricity therefrom.
  • the compressed cooling air stream 36 is produced from the second compressed air stream 34 that has been extracted from the compressor 1 2.
  • the second compressed air stream 34 is directed through a cooling means 20 to produce the compressed cooling air stream 36.
  • the cooling means 20 may use water, air, or other cooling mediums to reduce the temperature of the second compressed air stream 34.
  • the extracting and cooling of the second compressed air stream 34 to produce the compressed cooling air stream 36 is not thermodynamically efficient because the stream 34 is a result of a nearly adiabatic compression.
  • the stream 34 has been heated to a temperature higher than what is needed to cool the turbine 16 and requires cooling to produce the compressed cooling air stream 36. It would be more efficient to produce cooling air in a more isothermal process and thereby reducing the power required for producing the compressed cooling air stream.
  • the extracting of the second compressed air stream 34 to produce the compressed cooling stream is also detrimental to the overall power produced by the combustion turbine system 10.
  • the overall power of the system 10 is dependent upon the volume of airflow through the turbine 1 6.
  • the present invention provides a process and system for use in operating a combustion turbine system having a system air compressor, a combustor. and a turbine.
  • An auxiliary air compressor system receives an air stream and produces a compressed cooling air stream therefrom. The cooling air stream is then directed to the combustion turbine system and is used to coo* the turbine.
  • FIG. 1 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with compressed air produced in the system compressor.
  • Figure 2 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with a compressed cooling air stream from an auxiliary compressor system powered by an engine according to an embodiment of the invention.
  • Figure 3 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with a compressed cooling air stream from a multistage auxiliary compressor system having intercooiers between the stages and powered by a steam turbine according to an embodiment of the invention.
  • Figure 4 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with a compressed cooling air stream from a multistage auxiliary compressor system that is powered by the combustion turbine system according to an embodiment of the invention.
  • Figure 5 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with a compressed cooling air stream from a multistage auxiliary compressor system that is powered by an auxiliary combustion turbine system according to an embodiment of the invention.
  • the turbine 1 6 is cooled by a compressed cooling air stream 50 that has been compressed by an auxiliary compressor 54.
  • the auxiliary compressor 54 receives an air stream 52 and compresses it to form a heated compressed air stream 60.
  • the auxiliary compressor 54 may be powered by a motor 56 via a shaft 58, as shown in Figure 2.
  • the heated compressed air stream 60 is cooled in an aftercooler 62 to produce the compressed cooling air stream 50.
  • Other embodiments of the invention may not have an aftercooler
  • the compressed cooling air stream 50 is produced using an adiabatic compression, like the compressed cooling air stream 34 shown in Prior Art Figure 1 .
  • an adiabatic compression like the compressed cooling air stream 34 shown in Prior Art Figure 1 .
  • This embodiment of the invention has increased overall power generation by the combustion turbine system 1 0 when the power required by the auxiliary compressor 54 is less than the additional power produced by the turbine 1 6 because of all the air flow from the compressor 1 2 is now directed to turbine 1 6.
  • the turbine 16 is cooled by a compressed cooling air stream 70 produced by compressing an air stream 72 in an auxiliary multistage compressor 74.
  • the auxiliary multistage compressor 74 is comprised of three serially arranged compressing stages 78, 80, and 82. Between the adjacent compressing stages 78 and 80, the air stream is cooled by an intercooler 84. Likewise, between the adjacent compressing stages 80 and 82, the air stream is cooled by an intercooler 86.
  • the intercoolers 84 and 86 may be integral or external to the auxiliary multistage compressor 74.
  • the embodiment of the invention shown in Figure 3 has a higher overall energy generation than the prior art combustion turbine system shown in Prior Art Figure 1 .
  • the use of intercoolers 84 and 86 in the auxiliary multistage compressor 74 result in a compressed cooling air stream 70 produced by a more efficient, more isothermal compression compared to the adiabatic compression of the compressor 12. Further, the air flow through the turbine 16 is increased, resulting in more power generation.
  • Other embodiments of the invention may have more or less compressing stages, may have more or less intercoolers, and may not have an aftercooler.
  • the auxiliary multistage compressor 74 is provided rotating shaft power via shaft 90 from a steam turbine 92.
  • the steam turbine 92 receives steam flow 94 and expands it to produce an expanded steam flow 96 and the rotating shaft power.
  • the turbine 1 6 is cooled by a compressed cooling air stream 100 produced by compressing an air stream 102 in an auxiliary multistage compressor 104 having stages 106 and 1 10.
  • the air stream 102 is received by the first compressing stage 106, compressed, cooled by an intercooler 108, and compressed again in the second compressing stage 1 10 to produce the compressed cooling air stream 100.
  • the intercooler 108 may be integral or external to the auxiliary multistage compressor 104.
  • Other embodiments of the invention may have more or less stages, may have more or less intercoolers, and may have an aftercooler.
  • the auxiliary multistage compressor 104 is provided rotating shaft power to its shaft 1 12 from the shaft 18 of the combustion turbine system 1 0.
  • a power transfer means 1 14 transfers the rotating shaft power from shaft 1 8 to shaft 1 1 2.
  • the power transfer means 1 1 4 may be a clutch, a hydraulic coupling, a gear, or any other suitable means. Other embodiments of the invention may not require a power transfer means 1 14.
  • the turbine 16 is cooled by a compressed cooling air stream 20 produced by compressing an air stream 122 in an auxiliary multistage compressor 124 having stages 126 and 1 30.
  • the air stream 122 is received by the first compressing stage 126, compressed, cooled by an intercooler 128, and compressed again in the second compressing stage 1 30 to produce the compressed cooling air stream 120.
  • the intercooler 1 28 may be integral or external to the auxiliary multistage compressor 104.
  • the stages 1 26 and 1 30 receive rotating shaft power to operate via shaft 1 32.
  • Other embodiments of the invention may have more or less stages, may have more or less intercoolers, and may have an aftercooler.
  • the auxiliary multistage compressor 124 is provided rotating shaft power via shaft 132 from an auxiliary combustion turbine system 1 36.
  • the auxiliary combustion turbine system 1 36 is comprised of a compressor 1 38, a combustor 140 and a turbine 142 that are operationally connected.
  • the compressor 1 38 receives an air stream 1 44 and compresses it to produce compressed air stream 146.
  • the combustor 140 receives the compressed air stream 1 46 along with fuel stream 148 and combusts them to produce a combustion emission stream 150.
  • the turbine 142 receives the combustion emission stream 150 and expands it to produce an expanded emission stream 1 52 and rotating shaft power in shaft 1 32.
  • Other embodiments of the invention may use other suitable arrangements of the auxiliary combustion system, including cooling the turbine 142 using compressed air from a source other than the compressor 1 38.
  • the present invention may be practiced with an auxiliary compressor that includes any number of compressing stages, intercoolers, and aftercoolers.
  • the invention may use any suitable means of providing rotating shaft power to the auxiliary compressor beyond the means previously discussed that include the electrical motor 56, the steam turbine 94, the combustion turbine system 1 0 itself, and the auxiliary combustion turbine system 1 36. Therefore, the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof and, accordingly, reference should be made to the appended claims, rather than to the foregoing specification, as indicating the scope of the invention.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

A combustion turbine system (10) is provided with compressed cooling air (50) by an auxiliary air compressor (54) system. The combustion turbine system (10) has a system air compressor (12), a combustor (14) and a turbine (16). The auxiliary air compressor (59) system receives an air stream and produces a compressed cooling air stream (50) therefrom. The cooling air stream (50) is then directed to the combustion turbine system (10) and is used to cool the turbine (16).

Description

METHOD AND APPARATUS FOR COOLING A TURBINE WITH COMPRESSED COOLING AIR FROM AN AUXILIARY COMPRESSOR
SYSTEM
BACKGROUND OF THE INVENTION
The present invention relates to providing compressed cooling air to turbines in combustion turbine systems.
As shown in Prior Art Figure 1 , the prior art discloses that a turbine 1 6 in a combustion turbine system 1 0 is cooled by a compressed cooling air stream 36 from a compressor 1 2 of the system. The combustion turbine system 10 is comprised of the compressor 1 2, a combustor 14 and the turbine 1 6 that are operationally connected. The compressor 1 2 receives an air flow 24 and compresses it to produce a first compressed air stream 26 and a second compressed air stream 34. The first compressed air stream 26 is directed, along with a fuel stream 28, into the combustor 1 4. The streams are combusted in the combustor 1 4 to produce a combustion emission stream 30. The combustion emission stream 30 is directed to the turbine 1 6, which expands the stream 30, thereby producing expanded emissions 32 and rotating a shaft 1 8. The rotating shaft 1 8 provides rotating shaft power to the compressor 1 2 for its operation and to the generator 22 which produces electricity therefrom.
The compressed cooling air stream 36 is produced from the second compressed air stream 34 that has been extracted from the compressor 1 2. The second compressed air stream 34 is directed through a cooling means 20 to produce the compressed cooling air stream 36. The cooling means 20 may use water, air, or other cooling mediums to reduce the temperature of the second compressed air stream 34.
The extracting and cooling of the second compressed air stream 34 to produce the compressed cooling air stream 36 is not thermodynamically efficient because the stream 34 is a result of a nearly adiabatic compression. The stream 34 has been heated to a temperature higher than what is needed to cool the turbine 16 and requires cooling to produce the compressed cooling air stream 36. It would be more efficient to produce cooling air in a more isothermal process and thereby reducing the power required for producing the compressed cooling air stream.
The extracting of the second compressed air stream 34 to produce the compressed cooling stream is also detrimental to the overall power produced by the combustion turbine system 10. The overall power of the system 10 is dependent upon the volume of airflow through the turbine 1 6. By not using the second compressed air stream 34 to combust the fuel stream 28 and form the emission stream 30, the air flow through the turbine is reduced, resulting in a power reduction.
It is therefore desirable to provide an alternative method and apparatus to providing compressed cooling air to the combustion turbine system for cooling the turbine.
SUMMARY OF THE INVENTION The present invention provides a process and system for use in operating a combustion turbine system having a system air compressor, a combustor. and a turbine. An auxiliary air compressor system receives an air stream and produces a compressed cooling air stream therefrom. The cooling air stream is then directed to the combustion turbine system and is used to coo* the turbine.
BRIEF DESCRIPTION OF THE DRAWINGS Prior Art Figure 1 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with compressed air produced in the system compressor.
Figure 2 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with a compressed cooling air stream from an auxiliary compressor system powered by an engine according to an embodiment of the invention.
Figure 3 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with a compressed cooling air stream from a multistage auxiliary compressor system having intercooiers between the stages and powered by a steam turbine according to an embodiment of the invention.
Figure 4 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with a compressed cooling air stream from a multistage auxiliary compressor system that is powered by the combustion turbine system according to an embodiment of the invention.
Figure 5 shows a schematic diagram of a combustion turbine system having a turbine that is cooled with a compressed cooling air stream from a multistage auxiliary compressor system that is powered by an auxiliary combustion turbine system according to an embodiment of the invention.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Now referring to the figures, wherein like reference numerals refer to like elements, and in particular to Figure 2, the turbine 1 6 is cooled by a compressed cooling air stream 50 that has been compressed by an auxiliary compressor 54. The auxiliary compressor 54 receives an air stream 52 and compresses it to form a heated compressed air stream 60. In a preferred embodiment of the invention, the auxiliary compressor 54 may be powered by a motor 56 via a shaft 58, as shown in Figure 2. The heated compressed air stream 60 is cooled in an aftercooler 62 to produce the compressed cooling air stream 50. Other embodiments of the invention may not have an aftercooler
62.
The compressed cooling air stream 50 is produced using an adiabatic compression, like the compressed cooling air stream 34 shown in Prior Art Figure 1 . However, the embodiment of the invention shown in Figure
2 has an increased air flow through the turbine 1 6. This embodiment of the invention has increased overall power generation by the combustion turbine system 1 0 when the power required by the auxiliary compressor 54 is less than the additional power produced by the turbine 1 6 because of all the air flow from the compressor 1 2 is now directed to turbine 1 6.
Other embodiments of the invention may use other arrangements of auxiliary compressors and other means for powering auxiliary compressors. Now referring to Figure 3, the turbine 16 is cooled by a compressed cooling air stream 70 produced by compressing an air stream 72 in an auxiliary multistage compressor 74. The auxiliary multistage compressor 74 is comprised of three serially arranged compressing stages 78, 80, and 82. Between the adjacent compressing stages 78 and 80, the air stream is cooled by an intercooler 84. Likewise, between the adjacent compressing stages 80 and 82, the air stream is cooled by an intercooler 86. The intercoolers 84 and 86 may be integral or external to the auxiliary multistage compressor 74. By cooling the air stream between compressing stages, the compression is more isothermal than the adiabatic compression of the compressor 54. The compressed cooling air stream 70 may also be further cooled by an aftercooler 76.
The embodiment of the invention shown in Figure 3 has a higher overall energy generation than the prior art combustion turbine system shown in Prior Art Figure 1 . The use of intercoolers 84 and 86 in the auxiliary multistage compressor 74 result in a compressed cooling air stream 70 produced by a more efficient, more isothermal compression compared to the adiabatic compression of the compressor 12. Further, the air flow through the turbine 16 is increased, resulting in more power generation. Other embodiments of the invention may have more or less compressing stages, may have more or less intercoolers, and may not have an aftercooler.
The auxiliary multistage compressor 74 is provided rotating shaft power via shaft 90 from a steam turbine 92. The steam turbine 92 receives steam flow 94 and expands it to produce an expanded steam flow 96 and the rotating shaft power. Now referring to Figure 4, the turbine 1 6 is cooled by a compressed cooling air stream 100 produced by compressing an air stream 102 in an auxiliary multistage compressor 104 having stages 106 and 1 10. The air stream 102 is received by the first compressing stage 106, compressed, cooled by an intercooler 108, and compressed again in the second compressing stage 1 10 to produce the compressed cooling air stream 100. The intercooler 108 may be integral or external to the auxiliary multistage compressor 104. Other embodiments of the invention may have more or less stages, may have more or less intercoolers, and may have an aftercooler.
The auxiliary multistage compressor 104 is provided rotating shaft power to its shaft 1 12 from the shaft 18 of the combustion turbine system 1 0. A power transfer means 1 14 transfers the rotating shaft power from shaft 1 8 to shaft 1 1 2. The power transfer means 1 1 4 may be a clutch, a hydraulic coupling, a gear, or any other suitable means. Other embodiments of the invention may not require a power transfer means 1 14.
Now referring to Figure 5, the turbine 16 is cooled by a compressed cooling air stream 20 produced by compressing an air stream 122 in an auxiliary multistage compressor 124 having stages 126 and 1 30. The air stream 122 is received by the first compressing stage 126, compressed, cooled by an intercooler 128, and compressed again in the second compressing stage 1 30 to produce the compressed cooling air stream 120. The intercooler 1 28 may be integral or external to the auxiliary multistage compressor 104. The stages 1 26 and 1 30 receive rotating shaft power to operate via shaft 1 32. Other embodiments of the invention may have more or less stages, may have more or less intercoolers, and may have an aftercooler.
The auxiliary multistage compressor 124 is provided rotating shaft power via shaft 132 from an auxiliary combustion turbine system 1 36. The auxiliary combustion turbine system 1 36 is comprised of a compressor 1 38, a combustor 140 and a turbine 142 that are operationally connected. The compressor 1 38 receives an air stream 1 44 and compresses it to produce compressed air stream 146. The combustor 140 receives the compressed air stream 1 46 along with fuel stream 148 and combusts them to produce a combustion emission stream 150. The turbine 142 receives the combustion emission stream 150 and expands it to produce an expanded emission stream 1 52 and rotating shaft power in shaft 1 32. Other embodiments of the invention may use other suitable arrangements of the auxiliary combustion system, including cooling the turbine 142 using compressed air from a source other than the compressor 1 38.
The present invention may be practiced with an auxiliary compressor that includes any number of compressing stages, intercoolers, and aftercoolers.
Further, the invention may use any suitable means of providing rotating shaft power to the auxiliary compressor beyond the means previously discussed that include the electrical motor 56, the steam turbine 94, the combustion turbine system 1 0 itself, and the auxiliary combustion turbine system 1 36. Therefore, the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof and, accordingly, reference should be made to the appended claims, rather than to the foregoing specification, as indicating the scope of the invention.

Claims

1. A process for operating a first combustion turbine system comprising a system air compressor, a combustor, and a turbine being operationally connected together, comprising the steps of: a) directing an air stream into an auxiliary air compressor system to produce a compressed cooling air stream therefrom; and b) cooling the turbine with said compressed cooling air stream.
2. The process of claim 1 , further comprising the step of providing rotating shaft power to said auxiliary compressor system for the operation thereof via a motor.
3. The process of claim 1 , further comprising the step of providing rotating shaft power to said auxiliary compressor system for the operation thereof via a steam turbine system.
4. The process of claim 1 , further comprising the step of providing rotating shaft power to said auxiliary compressor system for the operation thereof via the first combustion turbine system.
5. The process of claim 1 , further comprising the step of providing rotating shaft power to said auxiliary compressor system for the operation thereof via a second combustion turbine system.
6. The process of claim 1 , wherein said directing said air stream step further comprises the steps of: a) compressing said air stream to produce a compressed air stream; and b) cooling said compressed air stream to produce said compressed cooling air stream.
7. The process of claim 1 , wherein said directing said air stream step further comprises the step of repeatedly compressing and cooling a plurality of times said air stream until said compressed cooling air stream is produced.
8. The process of claim 7, further comprising the step of providing rotating shaft power to said auxiliary compressor system for the operation thereof via a motor.
9. The process of claim 7, further comprising the step of providing rotating shaft power to said auxiliary compressor system for the operation thereof via a steam turbine system.
10. The process of claim 7, further comprising the step of providing rotating shaft power to said auxiliary compressor system for the operation thereof via the first combustion turbine system.
1 1 . The process of claim 7, further comprising the step of providing rotating shaft power to said auxiliary compressor system for the operation thereof via a second combustion turbine system.
1 2. A power generating system comprising: a) auxiliary compressor means for receiving rotating shaft power and an auxiliary air stream, and producing a compressed cooling air stream therefrom; and b) a first combustion turbine system comprising: i) first compressor means for compressing a compressor air stream to produce a compressed air stream; ii) combustor means for receiving and combusting a fuel stream and said compressed air stream to produce a combustion emission stream; and iii) turbine means for receiving and expanding said combustion emission stream to produce shaft power and an expanded emission stream, and for receiving said compressed cooling air stream to cool said turbine means.
1 3. The power generating system of claim 1 2, wherein said auxiliary compressor means comprises: a) compressing stage means for compressing said auxiliary air stream; and b) cooling stage means for receiving said auxiliary air stream from said compressing stage means and cooling said auxiliary air stream.
14. The power generating system of claim 1 2, wherein said auxiliary compressor means comprises: a) a plurality of serially arranged compressing stage means, ending with a final compressing stage means, for receiving, compressing, and discharging said auxiliary air stream; and b) intercooling means for cooling said auxiliary air stream flowing between at least a pair of adjacent compressing stage means. '
1 5. The power generating system of claim 14, wherein said auxiliary compressor means further comprises aftercooler means for receiving said auxiliary air stream from said final compressing stage means and cooling said auxiliary air stream.
1 6. The power generating system of claim 1 2, further comprising a motor for supplying rotating shaft power to said auxiliary compressor means.
1 7. The power generating system of claim 1 2, further comprising a steam turbine system for supplying rotating shaft power to said auxiliary compressor means.
1 8. The power generating system of claim 1 2, further comprising means for delivering said rotating shaft power from said first combustion turbine system to said auxiliary compressor means.
* 1 9. The power generating system of claim 1 2, further comprising a second combustion turbine system for supplying rotating shaft power to said auxiliary compressor means.
PCT/US1998/008628 1997-05-13 1998-04-29 Method and apparatus for cooling a turbine with compressed cooling air from an auxiliary compressor system WO1998051917A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US85542897A 1997-05-13 1997-05-13
US08/855,428 1997-05-13

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Publication Number Publication Date
WO1998051917A1 true WO1998051917A1 (en) 1998-11-19

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AR (1) AR012693A1 (en)
TW (1) TW394822B (en)
WO (1) WO1998051917A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1148220A3 (en) * 2000-04-19 2003-01-22 General Electric Company Combustion turbine cooling media supply system and related method
WO2011026732A1 (en) * 2009-09-03 2011-03-10 Alstom Technology Ltd. Gas turbine group

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8079802B2 (en) * 2008-06-30 2011-12-20 Mitsubishi Heavy Industries, Ltd. Gas turbine
TWI397634B (en) * 2010-12-06 2013-06-01 China Steel Corp On-line monitor method of multi-stage compressor
KR101933585B1 (en) * 2012-07-25 2018-12-28 한화에어로스페이스 주식회사 A gas turbine apparatus
US9822670B2 (en) * 2015-03-19 2017-11-21 General Electric Company Power generation system having compressor creating excess air flow and turbo-expander for cooling inlet air
US9828887B2 (en) * 2015-03-19 2017-11-28 General Electric Company Power generation system having compressor creating excess air flow and turbo-expander to increase turbine exhaust gas mass flow
US9863284B2 (en) * 2015-03-19 2018-01-09 General Electric Company Power generation system having compressor creating excess air flow and cooling fluid injection therefor
US20160273394A1 (en) * 2015-03-19 2016-09-22 General Electric Company Power generation system having compressor creating excess air flow and eductor augmentation

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2064008A (en) * 1979-11-07 1981-06-10 Alsthom Atlantique A Cooling System for a Gas Turbine Engine
US4991394A (en) * 1989-04-03 1991-02-12 Allied-Signal Inc. High performance turbine engine
US5313783A (en) * 1992-03-31 1994-05-24 Asea Brown Boveri Ltd. Gas turbine plant
US5321944A (en) * 1992-01-08 1994-06-21 Ormat, Inc. Power augmentation of a gas turbine by inlet air chilling
US5724806A (en) * 1995-09-11 1998-03-10 General Electric Company Extracted, cooled, compressed/intercooled, cooling/combustion air for a gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2064008A (en) * 1979-11-07 1981-06-10 Alsthom Atlantique A Cooling System for a Gas Turbine Engine
US4991394A (en) * 1989-04-03 1991-02-12 Allied-Signal Inc. High performance turbine engine
US5321944A (en) * 1992-01-08 1994-06-21 Ormat, Inc. Power augmentation of a gas turbine by inlet air chilling
US5313783A (en) * 1992-03-31 1994-05-24 Asea Brown Boveri Ltd. Gas turbine plant
US5724806A (en) * 1995-09-11 1998-03-10 General Electric Company Extracted, cooled, compressed/intercooled, cooling/combustion air for a gas turbine engine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1148220A3 (en) * 2000-04-19 2003-01-22 General Electric Company Combustion turbine cooling media supply system and related method
WO2011026732A1 (en) * 2009-09-03 2011-03-10 Alstom Technology Ltd. Gas turbine group
CH701803A1 (en) * 2009-09-03 2011-03-15 Alstom Technology Ltd Gas turbine group and method for operating such a gas turbine group.
US8875483B2 (en) 2009-09-03 2014-11-04 Alstom Technology Ltd Gas turbine generator set

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TW394822B (en) 2000-06-21
JPH10317989A (en) 1998-12-02
AR012693A1 (en) 2000-11-08

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