US3747336A - Steam injection system for a gas turbine - Google Patents

Steam injection system for a gas turbine Download PDF

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Publication number
US3747336A
US3747336A US00239273A US3747336DA US3747336A US 3747336 A US3747336 A US 3747336A US 00239273 A US00239273 A US 00239273A US 3747336D A US3747336D A US 3747336DA US 3747336 A US3747336 A US 3747336A
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United States
Prior art keywords
liner
steam
air
combustion
tempering
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Expired - Lifetime
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US00239273A
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English (en)
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N Dibelius
R Johnson
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General Electric Co
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General Electric Co
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • F23L7/002—Supplying water
    • F23L7/005—Evaporated water; Steam
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F02C3/305—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube

Definitions

  • ABSTRACT Steam injection nozzles for augmenting the power output of a gas turbine are arranged to selectively inject steam into the combustion liner downstream of the combustion reaction zone.
  • the steam injection nozzles are spaced from but aligned with selected air holes in the liner, so that the injected steam restricts entry of air into the liner when the steam is on. Air is admitted through the holes into the liner when the steam is off, thus maintaining the proper pressure drop across the liner in either wet or dry operating mode.
  • This invention relates generally to steam injection systems for gas turbines and more particularly to steam injection systems for gas turbine combustors of the type which employ a perforated liner inside a casing supplied with combustion and dilution air.
  • one object of the present invention is to provide a gas turbine combustion system which maintains proper pressure drop across the combustion liner either with or without steam injection.
  • the invention comprises a combustion liner disposed in a casing supplied with air, the liner having combustion air holes and downstream tempering air holes.
  • Stream spray nozzles are disposed between the casing and the liner. The nozzles are aligned with and spaced from selected tempering holes. Steam injected through the nozzles restricts air flow through the holes when steam is on and admits flow of additional tempering air through the holes when the steam is off. Some steam spills to flow into the combustion reaction zone. This spillage steam also insures a seal so that no air enters the hole, thereby forcing air thru fewer liner holes. Accordingly, this causes a greater pressure drop to compensate for the increased back pressure when steam is flowing.
  • FIG. 1 is a horizontal elevation, partly in section, of a single combustion chamber in a gas turbine
  • FIGS. 2 and 3 are enlarged cross-sections illustrating a steam injection nozzle under two modes of operation
  • Combustion chamber 1 is of the type where the compressed air from the compressor (not shown) is directed in a reverse flow.
  • the reverse flow of such a combustion chamber is well known in the art and provides the advantage of heating the compressed air before its use in the combustion processes.
  • Combustion chamber 1 is comprised of a generally cylindrical outer casing 2 to which is attached the casing 3.
  • Casing 3 in turn connects with the turbine section (not shown).
  • the outer casing end cover 4 closes off the end of outer casing 2 opposite the casing 3 such that the volume within outer casing 2 is sealed from the atmosphere.
  • it is within the liner 5 at the head end or combustion reaction zone 6 where the combustion process takes place in an operating combustor for gas turbines.
  • An annular air space 8 surrounds the liners S and 7 in order to accommodate the flow of the compressed air.
  • the liner end cap 9 which accommodates the fuel nozzle generally indicated as 10.
  • the liner end cap 9 is generally in the shape of a truncated cone, the top of which is for the accommodation therein of the fuel nozzle assembly 10.
  • the air swirler assembly 11 is attached to the cap 9 but may also be attached to the fuel nozzle.
  • the fuel nozzle assembly 10 may be any convenient type known to the art which can be accommodated in the head end of the liner 5 and particularly in the end cap 9.
  • Fuel nozzle 10 is of the variety which is capable of atomizing hydrocarbon fuels.
  • the fuel nozzle 10 may be of the air atomizing type or pressure atomizing type. Alternatively it can be of the non-atomizing type adapted to inject gaseous fuel.
  • tehre are two rows of combustion air holes.
  • a first row 12 is comprised of 8 holes circumferentially spaced'about the liner 5.
  • a second row 14 is again comprised of 8 holes circumferentially spaced about liner 5. Rows 12 and 14 are within combustion reaction zone 6.
  • the thermal soaking region of the liner 5 Following the row of holes 14 downstream (in relation to the flow of combustion products) in an axial direction, is the thermal soaking region of the liner 5. This is indicated as 15 on FIG. 1.
  • the thermal soaking region 15 is closed in that there are no large circumferentially spaced holes along this axial length of liner; however, louvers or slits for metal cooling air are positioned throughout the length of liner 5, but are not shown for clarity.
  • the louvers are utilized for cooling the liner and the air which enters the louvers does not contribute to the combustion process to an important degree.
  • tempering air holes 16 Positioned at the end of the thermal soaking region are a plurality of circumferentially spaced tempering air holes 16.
  • the actual size and number of tempering air holes 16 will depend upon the amount of tempering air to be added to the combustion products as they leave the soaking region 15.
  • the tempering region of the liner 5 is indicated on FIG. 1 as 18 and extends generally from the tempering air holes 16 to the first stage nozzle.
  • the purpose of the tempering air holes 16 is to allow a portion of the compressed air which is relatively cool as compared to the hot combustion products to temper the combustion products before the overall air-combustion product mixture enters the first stage nozzle.
  • Tempering holes 16 are large enough to allow sufficient penetration of the cooler tempering air into the combustion products so that the desired first stage turbine inlet temperature is achieved.
  • a first set of steam injection nozzles 19 may be disposed in the annular space between casing 2 and liner 5 and selectively supplied with a source of steam. Too much steam injected in nozzles 19 would tend to degrade the combustion reaction taking place in zone 6, since the steam from nozzles l9 enters along with the air through combustion holes l2, 14 into the reaction zone.
  • a second set of steam injection nozzles 20 are circumferentially spaced around the liner and supplied with a source of steam through pipes 21.
  • This steam may be supplied from the same source as nozzles 19 and added through nozzles 19, 20 either at the same time or separately. Control of this steam is symbolically shown by valves 21a while control of nozzles 19 steam is symbolically shown by valves 19a.
  • Nozzles 10 are spaced from and aligned with the tempering air holes 22.
  • Nozzles 20 are of the type designed to give a wide angle solid-cone spray so as to substantially blanket the open area of holes 22.
  • a suitable nozzle for this purpose is known as solid-cone vortex nozzle and may be commercially obtained from the Monarch Nozzle Co.
  • the number of air tempering holes 22 which are provided with spray nozzles 20 and the number of tempering holes 16 which have no spray nozzles depend upon the particular design.
  • the restriction of flow area when holes 16 only are admitting air should be such as to compensate for the volumetric expansion of the injected steam and back pressure due to choked turbine nozzle.
  • FIGS. 2 and 3 show enlarged views of one of the nozzles 20 and one of the holes 22. Here the cooling louvers 5a in the liner wall are seen. When steam is not being injected, air flows toward the combustion reaction zone 6 and also flows through hole 22 to enter the tempering zone 18 downstream of the combustion zone.
  • hole 22 is substantially closed off from the entry of air. Some of the overflow steam may be blown toward the combustion zone permitting partial air admission depending upon the design. This overflow steam aids in nitric oxide abatement.
  • a gas turbine having at least one combustion chamber comprising an elongated casing supplied with air and adapted to burn fuel in a liner spaced within said casing, the liner including combustion air holes supplying air to a combustion reaction zone and a plurality of tempering air holes supplying air to a tempering region in the liner and downstream from the combustion reaction zone, the improvement comprising:
  • conduit means supplied with a source of steam for injection into said tempering region
  • a plurality of steam nozzles mounted on said casing and directed into the space between said casing and said liner, said nozzles being aligned with and spaced from selected tempering air holes, said nozzles being adapted to spray steam so as to substantially fill the open area of said selected tempering air holes.
  • a steam injection system for a gas turbine comprismg:
  • At least one elongated combustion casing with an open end and a closed end and supplied with air at reaction zone near its closed end toward the open end of said casing and liner,
  • a plurality of steam injection nozzles equal to or fewer in number than said tempering air holes, said nozzles being mounted on the casing and directed into the space between the liner and easing, each nozzle being directed toward a selected one of said tempering air holes and adapted to substantially fill said hole, with steam and a conduit connected between a source of steam and said nozzles along with means to selectively supply steam through the conduit to said nozzles, whereby air is admitted through all of said air tempering holes when the steam is off, but primarily through a lesser number of the air tempering holes when steam is on.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US00239273A 1972-03-29 1972-03-29 Steam injection system for a gas turbine Expired - Lifetime US3747336A (en)

Applications Claiming Priority (1)

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US23927372A 1972-03-29 1972-03-29

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US (1) US3747336A (enrdf_load_stackoverflow)
JP (1) JPS497616A (enrdf_load_stackoverflow)
CA (1) CA962072A (enrdf_load_stackoverflow)
FR (1) FR2178160A1 (enrdf_load_stackoverflow)
GB (1) GB1380028A (enrdf_load_stackoverflow)
IT (1) IT981247B (enrdf_load_stackoverflow)
NL (1) NL7304307A (enrdf_load_stackoverflow)

Cited By (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2538134A1 (de) * 1974-08-27 1976-03-11 Mitsubishi Heavy Ind Ltd Oelbrenner
US4173118A (en) * 1974-08-27 1979-11-06 Mitsubishi Jukogyo Kabushiki Kaisha Fuel combustion apparatus employing staged combustion
US4382771A (en) * 1980-05-12 1983-05-10 Lola Mae Carr Gas and steam generator
US4625509A (en) * 1980-04-21 1986-12-02 Sheppard Sr Darrel J Combustion engine
US4893469A (en) * 1988-01-07 1990-01-16 Yasui Yamashita Steam and combustion gas engine
EP0372472A1 (en) * 1988-12-09 1990-06-13 Hitachi, Ltd. Method and device for starting a gas turbine
GB2228295A (en) * 1988-12-14 1990-08-22 Gen Electric Cooling a turbine engine
US5054279A (en) * 1987-11-30 1991-10-08 General Electric Company Water spray ejector system for steam injected engine
US5148668A (en) * 1990-01-31 1992-09-22 Asea Brown Boveri Ltd. Combined gas/steam turbine power station plant
US5239816A (en) * 1992-03-16 1993-08-31 General Electric Company Steam deflector assembly for a steam injected gas turbine engine
US5566542A (en) * 1994-08-24 1996-10-22 Westinghouse Electric Corporation Method for regulating and augmenting the power output of a gas turbine
US6085514A (en) * 1996-12-27 2000-07-11 Abb Alstom Power (Switzerland) Ltd. Method of steam cooling thermally highly loaded units of a gas-turbine group
US6116018A (en) * 1996-05-13 2000-09-12 Mitsubishi Heavy Industries, Ltd. Gas turbine plant with combustor cooling system
US6247316B1 (en) 2000-03-22 2001-06-19 Clean Energy Systems, Inc. Clean air engines for transportation and other power applications
WO2002014672A1 (en) * 2000-08-11 2002-02-21 Cheng Power Systems, Inc. Steam injection nozzle design of gas turbine combustion liners for enhancing power output and efficiency
US6389793B1 (en) 2000-04-19 2002-05-21 General Electric Company Combustion turbine cooling media supply system and related method
US6389814B2 (en) 1995-06-07 2002-05-21 Clean Energy Systems, Inc. Hydrocarbon combustion power generation system with CO2 sequestration
US6405521B1 (en) 2001-05-23 2002-06-18 General Electric Company Gas turbine power augmentation injection system and related method
US6446440B1 (en) 2000-09-15 2002-09-10 General Electric Company Steam injection and inlet fogging in a gas turbine power cycle and related method
US6499303B1 (en) 2001-04-18 2002-12-31 General Electric Company Method and system for gas turbine power augmentation
US6526758B2 (en) 2000-05-12 2003-03-04 General Electric Company Method and apparatus for power augmentation for gas turbine power cycles
US6530224B1 (en) 2001-03-28 2003-03-11 General Electric Company Gas turbine compressor inlet pressurization system and method for power augmentation
US6553768B1 (en) 2000-11-01 2003-04-29 General Electric Company Combined water-wash and wet-compression system for a gas turbine compressor and related method
US6622470B2 (en) 2000-05-12 2003-09-23 Clean Energy Systems, Inc. Semi-closed brayton cycle gas turbine power systems
US6662547B2 (en) * 2000-11-17 2003-12-16 Mitsubishi Heavy Industries, Ltd. Combustor
US20040065086A1 (en) * 2002-10-02 2004-04-08 Claudio Filippone Small scale hybrid engine (SSHE) utilizing fossil fuels
US20040083737A1 (en) * 2002-10-31 2004-05-06 Honeywell International Inc. Airflow modulation technique for low emissions combustors
US6868677B2 (en) 2001-05-24 2005-03-22 Clean Energy Systems, Inc. Combined fuel cell and fuel combustion power generation systems
US6945029B2 (en) 2002-11-15 2005-09-20 Clean Energy Systems, Inc. Low pollution power generation system with ion transfer membrane air separation
US6983605B1 (en) * 2000-04-07 2006-01-10 General Electric Company Methods and apparatus for reducing gas turbine engine emissions
US7021063B2 (en) 2003-03-10 2006-04-04 Clean Energy Systems, Inc. Reheat heat exchanger power generation systems
US20080178571A1 (en) * 2007-01-31 2008-07-31 Power Systems Manufacturing, Llc Inlet Bleed Heat and Power Augmentation For A Gas Turbine Engine
US7574870B2 (en) 2006-07-20 2009-08-18 Claudio Filippone Air-conditioning systems and related methods
US20090277184A1 (en) * 2008-05-06 2009-11-12 General Electric Company Turbomachine and a method for enhancing power efficiency in a turbomachine
US20100089021A1 (en) * 2008-10-14 2010-04-15 General Electric Company Method and apparatus of introducing diluent flow into a combustor
US20100092896A1 (en) * 2008-10-14 2010-04-15 General Electric Company Method and apparatus for introducing diluent flow into a combustor
US20100089020A1 (en) * 2008-10-14 2010-04-15 General Electric Company Metering of diluent flow in combustor
US20100089022A1 (en) * 2008-10-14 2010-04-15 General Electric Company Method and apparatus of fuel nozzle diluent introduction
US20100242488A1 (en) * 2007-11-29 2010-09-30 United Technologies Corporation gas turbine engine and method of operation
US7882692B2 (en) 2004-04-16 2011-02-08 Clean Energy Systems, Inc. Zero emissions closed rankine cycle power system
US20140013754A1 (en) * 2011-03-31 2014-01-16 Ilya Aleksandrovich Slobodyanskiy Power augmentation system with dynamics damping
US9279369B2 (en) 2013-03-13 2016-03-08 General Electric Company Turbomachine with transition piece having dilution holes and fuel injection system coupled to transition piece
EP3054213A1 (en) * 2015-02-06 2016-08-10 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor and steam injected gas turbine
US20160369751A1 (en) * 2015-06-22 2016-12-22 Chun-Ting Chen Internal combustion engine using water as auxiliary power
US11203972B2 (en) * 2018-03-07 2021-12-21 Doosan Heavy Industries & Construction Co., Ltd. Gas turbine and method of operating the same
US11459948B2 (en) * 2020-02-26 2022-10-04 Mitsubishi Heavy Industries, Ltd. Gas turbine plant
US11879364B2 (en) * 2014-11-06 2024-01-23 Powerphase International, Llc Gas turbine efficiency and power augmentation improvements utilizing heated compressed air
US12072100B1 (en) * 2023-11-07 2024-08-27 General Electric Company Combustor for a gas turbine engine
US12092023B1 (en) * 2023-03-14 2024-09-17 Rtx Corporation Steam cooling turbine engine combustor wall
EP4443056A1 (en) * 2023-03-14 2024-10-09 RTX Corporation Introducing steam with quench air into turbine engine combustor
US20250251129A1 (en) * 2024-02-01 2025-08-07 General Electric Company Gas turbine engine having a steam generating system providing steam to a combustor

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JPS50146707A (enrdf_load_stackoverflow) * 1974-05-20 1975-11-25
JPS5844925B2 (ja) * 1974-11-08 1983-10-06 川崎重工業株式会社 カキユウボイラノ フカジヨウシヨウカソクホウホウ
JPS5154753A (enrdf_load_stackoverflow) * 1974-11-09 1976-05-14 Tokyo Keiki Kk
JPS5477807U (enrdf_load_stackoverflow) * 1977-11-14 1979-06-02
DE3545524C2 (de) * 1985-12-20 1996-02-29 Siemens Ag Mehrstufenbrennkammer für die Verbrennung von stickstoffhaltigem Gas mit verringerter NO¶x¶-Emission und Verfahren zu ihrem Betrieb
JPS63167067U (enrdf_load_stackoverflow) * 1987-04-15 1988-10-31
JPH0219839U (enrdf_load_stackoverflow) * 1988-07-22 1990-02-09
GB2446650A (en) * 2007-02-16 2008-08-20 Noel Christopher Metcalfe Water augmented power enhancement of internal combustion or gas turbine engines

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US3088280A (en) * 1959-04-17 1963-05-07 Rolls Royce Reducing smoke in gas turbine engine exhaust
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Cited By (79)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4173118A (en) * 1974-08-27 1979-11-06 Mitsubishi Jukogyo Kabushiki Kaisha Fuel combustion apparatus employing staged combustion
DE2538134A1 (de) * 1974-08-27 1976-03-11 Mitsubishi Heavy Ind Ltd Oelbrenner
US4625509A (en) * 1980-04-21 1986-12-02 Sheppard Sr Darrel J Combustion engine
US4382771A (en) * 1980-05-12 1983-05-10 Lola Mae Carr Gas and steam generator
US5054279A (en) * 1987-11-30 1991-10-08 General Electric Company Water spray ejector system for steam injected engine
US4893469A (en) * 1988-01-07 1990-01-16 Yasui Yamashita Steam and combustion gas engine
EP0372472A1 (en) * 1988-12-09 1990-06-13 Hitachi, Ltd. Method and device for starting a gas turbine
US5121596A (en) * 1988-12-09 1992-06-16 Hitachi, Ltd. Method of starting gas turbine
GB2228295A (en) * 1988-12-14 1990-08-22 Gen Electric Cooling a turbine engine
US4982564A (en) * 1988-12-14 1991-01-08 General Electric Company Turbine engine with air and steam cooling
GB2228295B (en) * 1988-12-14 1992-12-16 Gen Electric Cooling a turbine engine
US5148668A (en) * 1990-01-31 1992-09-22 Asea Brown Boveri Ltd. Combined gas/steam turbine power station plant
US5239816A (en) * 1992-03-16 1993-08-31 General Electric Company Steam deflector assembly for a steam injected gas turbine engine
US5566542A (en) * 1994-08-24 1996-10-22 Westinghouse Electric Corporation Method for regulating and augmenting the power output of a gas turbine
US7043920B2 (en) 1995-06-07 2006-05-16 Clean Energy Systems, Inc. Hydrocarbon combustion power generation system with CO2 sequestration
US6389814B2 (en) 1995-06-07 2002-05-21 Clean Energy Systems, Inc. Hydrocarbon combustion power generation system with CO2 sequestration
US20040003592A1 (en) * 1995-06-07 2004-01-08 Fermin Viteri Hydrocarbon combustion power generation system with CO2 sequestration
US6598398B2 (en) 1995-06-07 2003-07-29 Clean Energy Systems, Inc. Hydrocarbon combustion power generation system with CO2 sequestration
US6116018A (en) * 1996-05-13 2000-09-12 Mitsubishi Heavy Industries, Ltd. Gas turbine plant with combustor cooling system
US6085514A (en) * 1996-12-27 2000-07-11 Abb Alstom Power (Switzerland) Ltd. Method of steam cooling thermally highly loaded units of a gas-turbine group
US6247316B1 (en) 2000-03-22 2001-06-19 Clean Energy Systems, Inc. Clean air engines for transportation and other power applications
US6523349B2 (en) 2000-03-22 2003-02-25 Clean Energy Systems, Inc. Clean air engines for transportation and other power applications
US6983605B1 (en) * 2000-04-07 2006-01-10 General Electric Company Methods and apparatus for reducing gas turbine engine emissions
US6389793B1 (en) 2000-04-19 2002-05-21 General Electric Company Combustion turbine cooling media supply system and related method
US6481212B2 (en) 2000-04-19 2002-11-19 General Electric Company Combustion turbine cooling media supply system and related method
US6584779B2 (en) 2000-04-19 2003-07-01 General Electric Company Combustion turbine cooling media supply method
US6637183B2 (en) 2000-05-12 2003-10-28 Clean Energy Systems, Inc. Semi-closed brayton cycle gas turbine power systems
US6526758B2 (en) 2000-05-12 2003-03-04 General Electric Company Method and apparatus for power augmentation for gas turbine power cycles
US6824710B2 (en) 2000-05-12 2004-11-30 Clean Energy Systems, Inc. Working fluid compositions for use in semi-closed brayton cycle gas turbine power systems
US6622470B2 (en) 2000-05-12 2003-09-23 Clean Energy Systems, Inc. Semi-closed brayton cycle gas turbine power systems
US6910335B2 (en) 2000-05-12 2005-06-28 Clean Energy Systems, Inc. Semi-closed Brayton cycle gas turbine power systems
US20050236602A1 (en) * 2000-05-12 2005-10-27 Fermin Viteri Working fluid compositions for use in semi-closed Brayton cycle gas turbine power systems
WO2002014672A1 (en) * 2000-08-11 2002-02-21 Cheng Power Systems, Inc. Steam injection nozzle design of gas turbine combustion liners for enhancing power output and efficiency
US6370862B1 (en) * 2000-08-11 2002-04-16 Cheng Power Systems, Inc. Steam injection nozzle design of gas turbine combustion liners for enhancing power output and efficiency
US20020190137A1 (en) * 2000-08-11 2002-12-19 Cheng Dah Yu Steam injection nozzle design of gas turbine combustion liners for enhancing power output and efficiency
US6446440B1 (en) 2000-09-15 2002-09-10 General Electric Company Steam injection and inlet fogging in a gas turbine power cycle and related method
US6553768B1 (en) 2000-11-01 2003-04-29 General Electric Company Combined water-wash and wet-compression system for a gas turbine compressor and related method
US6662547B2 (en) * 2000-11-17 2003-12-16 Mitsubishi Heavy Industries, Ltd. Combustor
US6530224B1 (en) 2001-03-28 2003-03-11 General Electric Company Gas turbine compressor inlet pressurization system and method for power augmentation
US6499303B1 (en) 2001-04-18 2002-12-31 General Electric Company Method and system for gas turbine power augmentation
US6405521B1 (en) 2001-05-23 2002-06-18 General Electric Company Gas turbine power augmentation injection system and related method
US6868677B2 (en) 2001-05-24 2005-03-22 Clean Energy Systems, Inc. Combined fuel cell and fuel combustion power generation systems
US7047722B2 (en) * 2002-10-02 2006-05-23 Claudio Filippone Small scale hybrid engine (SSHE) utilizing fossil fuels
US20040065086A1 (en) * 2002-10-02 2004-04-08 Claudio Filippone Small scale hybrid engine (SSHE) utilizing fossil fuels
US20040083737A1 (en) * 2002-10-31 2004-05-06 Honeywell International Inc. Airflow modulation technique for low emissions combustors
US6826913B2 (en) * 2002-10-31 2004-12-07 Honeywell International Inc. Airflow modulation technique for low emissions combustors
US6945029B2 (en) 2002-11-15 2005-09-20 Clean Energy Systems, Inc. Low pollution power generation system with ion transfer membrane air separation
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GB1380028A (en) 1975-01-08
FR2178160A1 (enrdf_load_stackoverflow) 1973-11-09
JPS497616A (enrdf_load_stackoverflow) 1974-01-23
IT981247B (it) 1974-10-10
NL7304307A (enrdf_load_stackoverflow) 1973-10-02
CA962072A (en) 1975-02-04

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