US10385780B2 - Integrated dual fuel delivery system - Google Patents

Integrated dual fuel delivery system Download PDF

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Publication number
US10385780B2
US10385780B2 US15/079,560 US201615079560A US10385780B2 US 10385780 B2 US10385780 B2 US 10385780B2 US 201615079560 A US201615079560 A US 201615079560A US 10385780 B2 US10385780 B2 US 10385780B2
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Prior art keywords
fuel
divider
delivery system
gas
dual
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US15/079,560
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US20160281606A1 (en
Inventor
Fridolin HEYNEN
Inaki MAIZTEGUI
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Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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    • 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
    • F02C7/22—Fuel supply systems
    • 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
    • F02C7/22—Fuel supply systems
    • F02C7/222—Fuel flow conduits, e.g. manifolds
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
    • 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
    • F02C7/22—Fuel supply systems
    • F02C7/228—Dividing fuel between various burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M43/00—Fuel-injection apparatus operating simultaneously on two or more fuels, or on a liquid fuel and another liquid, e.g. the other liquid being an anti-knock additive
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses

Definitions

  • the present invention relates to a fuel delivery system, and more particularly the invention relates to dual fuel delivery system for a gas turbine engine.
  • Modern gas turbines may operate on a number of different fuels, such as various kinds of liquid and gaseous fuels. For this reason, power plants may have gas turbine engines that can operate with dual fuel capability, for example, natural gas and diesel fuel. In general, the choice of the operational fuel depends on the price, availability and operational parameters.
  • Gas turbines comprise various types of combustors configured to produce a hot gas by burning a fuel in a compressed air.
  • the fuel is introduced in the combustor using one or more fuel nozzles.
  • the nozzles usually have capabilities to inject a dual fuel.
  • Dual fuel has to be delivered to the fuel nozzles from the fuel source.
  • Design of such dual fuel delivery systems has various challenges such as: space constrains, vibrational instabilities and thermal expansions.
  • FIG. 2 shows a fuel delivery system 200 comprising two fuel ring pipes, 202 and 204 .
  • Each of the ring pipes, 202 and 204 supplies one type of the fuel, and each pipe has plurality of fuel feeds 206 which are connected to combustor burners (not shown) of a gas turbine.
  • combustor burners not shown
  • FIG. 3 shows dual fuel supply system 300 for a burner 312 having several (in this example three) injection nozzles 310 .
  • Two types of fuel, 302 and 304 are supplied to every nozzle 310 .
  • Fuel 302 is supplied via a first fuel line 306
  • second fuel 304 is supplied via a second fuel line 308 .
  • this fuel delivery system is not compact and it could suffer from thermal and vibrational instabilities.
  • One object of the present invention is to provide improved dual fuel delivery system in terms of the complexity and space saving.
  • Another object of the present invention is to provide improved dual fuel delivery system in terms of thermal and vibrational stability.
  • Yet another object of the present invention is to provide improved dual fuel system particularly adapted to substantially rectangular shaped burners.
  • a dual fuel delivery system for a gas turbine comprising: a main fuel line having a main fuel oil conduit and a main fuel gas conduit, wherein the main fuel gas conduit encloses, at least partially, the main fuel oil conduit, and a first fuel divider having a first fuel oil divider connected to the main fuel oil conduit and a first fuel gas divider connected to the main fuel gas conduit, wherein the first fuel gas divider encloses, at least partially, the first fuel oil divider.
  • the dual fuel delivery system further comprises at least one second fuel divider having a second fuel oil divider and a second fuel gas divider, wherein one outlet of the first fuel divider is connected to an inlet of the second fuel divider.
  • the dual fuel delivery system comprises two second fuel dividers.
  • the first fuel divider is positioned in a first plane and the second fuel divider is positioned in a second plane, and the first plane is different from the second plane . . . . In one preferred embodiment these two planes are substantially at degrees angle. This configuration is particularly advantageous regarding space saving inside a gas turbine.
  • both the first fuel oil divider and the first fuel gas divider have one inlet and two outlets.
  • the main fuel gas conduit comprises an extension means, preferably metallic bellows. This configuration is particularly advantageous regarding problem of thermal expansions.
  • the first fuel oil divider comprises at least one extension means, such as a metallic hose or an extension joint.
  • a connection between the main fuel oil conduit and the first fuel oil divider comprises a horizontal sliding guide, and/or a connection between the first fuel oil divider and the second fuel oil divider comprises a vertical sliding guide.
  • the dual fuel delivery system further comprises an injection head, which comprises at least one injection nozzle adapted to inject fuel oil and/or fuel gas, wherein the injection head is connected to the first fuel divider or the second fuel divider.
  • the injection head comprises plurality of injection sections, wherein every injection section is connected to one outlet of the first fuel divider or the second fuel divider.
  • the dual fuel delivery system comprises fuel manifold connected to the inlet of the main fuel line, and adapted to supply fuel gas and fuel oil to the main fuel line.
  • a gas turbine comprising dual fuel delivery system.
  • a gas turbine comprises a can combustor, a cooling air housing, and a burner adapted to receive the injection head, wherein the inlet of the main fuel line is positioned outside the can housing, the outlet of the main fuel line and the inlet to the first fuel divider are positioned between the can housing and the cooling air housing.
  • the present application also provides for a method for delivering dual fuel to the injection head inside the burner of the gas turbine comprising the dual fuel delivery system.
  • the method comprises following steps: supplying fuel oil and/or fuel gas to the main fuel line, dividing the fuel oil and/or the fuel gas in the first fuel divider, and guiding fuel oil and/or fuel gas to the injection head.
  • FIG. 1 is a schematic diagram of a gas turbine according to the invention.
  • FIG. 2 is a perspective view of dual ring fuel delivery system from prior art.
  • FIG. 3 is a schematic diagram of a fuel delivery system from prior art.
  • FIG. 4 is a schematic representation of a dual fuel delivery system according to one embodiment of the present invention.
  • FIG. 5 is a perspective view of a part of a dual fuel delivery system according to one embodiment of the present invention.
  • FIG. 6 is a perspective view of a dual fuel delivery system according to one embodiment of the present invention.
  • FIG. 7 is a perspective view of a part of a dual fuel delivery system according to one embodiment of the present invention.
  • FIG. 8 is a perspective view of a rectangular burner adapted to receive injection nozzle head.
  • FIG. 9 is a schematic representation of a dual fuel delivery system inside a gas turbine according to one embodiment the present invention.
  • FIG. 1 shows a schematic view of gas turbine engine 100 according to one embodiment of the invention.
  • the gas turbine 100 is comprised of a compressor 102 , which compresses a flow of air 116 .
  • the compressed air 118 is directed to a combustor 106 which may comprise several combustor cans and burners.
  • the compressed air 118 is mixed with fuel oil 112 or fuel gas 114 , and the mixture of air and fuel is ignited to create a flow of hot combustion gases 120 , which are directed to drive a turbine 104 .
  • the mechanical work produced in the turbine 104 drives the compressor 102 and load 110 via a shaft 122 .
  • Fuels 112 and 114 are delivered to the combustor 106 via a dual fuel delivery system 400 according to the invention.
  • FIG. 4 shows the dual fuel delivery system 400 according to the invention, which may be used with the gas turbine 100 .
  • the dual fuel delivery system 400 comprises a main fuel line 402 having a main fuel oil conduit 406 and a main fuel gas conduit 404 .
  • the conduits 404 and 406 are in the form of two concentric conduits, wherein the main fuel gas conduit 404 completely encloses the main fuel oil conduit 406 , except for the entry section of the conduit 406 .
  • the main fuel gas conduit 404 encloses at least partially the main fuel oil conduit 406 .
  • the dual fuel delivery system 400 comprises also a first fuel divider 408 , having a first fuel oil divider 412 connected to the main fuel oil conduit 406 and a first fuel gas divider 410 connected to the main fuel gas conduit 404 .
  • a fuel divider is a device for dividing a fuel flow, and it has one inlet and two or more outlets. The number of branches of the divider is equal to the number of the outlets. The fuel flow may be divided equally or non-equally among the branches.
  • the first fuel gas divider 410 encloses, at least partially, the first fuel oil divider 412 . In the preferred embodiment, shown in FIG. 4 , the first fuel gas divider 410 encloses completely the first fuel oil divider 412 .
  • Every branch of the fuel gas divider 410 is enclosing corresponding branch of the fuel oil divider 412 .
  • the corresponding branches may be in the form of the concentric conduits.
  • the fuel oil supply channel (main fuel oil line and fuel oil divider) is advantageously protected by the fuel gas supply channel (main fuel gas line and fuel gas divider) against the hot air stream.
  • the fuel divider 408 has one inlet and two outlets, but more outlets are also possible.
  • the dual fuel delivery system 400 may have a second fuel divider 414 .
  • the purpose of these dividers is to further divide fuel flows coming from the main line 402 .
  • the second dividers 414 may have one inlet and two outlets.
  • the second fuel divider 414 has a second fuel oil divider 420 and a second gas fuel divider 422 .
  • One outlet of the first fuel divider 408 is connected to an inlet of the second fuel divider 414 .
  • system 400 has one inlet 418 (main fuel line inlet) and four outlets 416 i.e. both of the fuels, fuel gas and fuel oil, may be separated in four separated flows.
  • the main fuel gas conduit 404 may comprise an extension means, preferably a metallic bellow 424 .
  • the first fuel oil divider 412 may have an extension means, such as at least one metallic hose 426 , or an expansion joint.
  • the divider 412 has two metallic hoses 426 , wherein one hose is comprised in every branch of the divider 412 .
  • Other combinations of bellows and hoses in the main line 402 and/or in the different branches of any of the dividers are also possible.
  • FIG. 4 is a schematic, simplified and two-dimensional representation of the dual fuel delivery system 400 .
  • the main fuel line 402 and fuel dividers 408 and 414 are not necessarily all positioned in one plane.
  • the fuel divider 408 is positioned in a first plane and the fuel divider 414 is positioned in a second plane.
  • FIG. 5 shows in more detail part of (and interior of) the dual fuel delivery system 400 according to one preferred embodiment of the present invention. Contrary to the example of FIG. 4 where the first fuel divider 408 and the second fuel divider 414 are positioned in one plane i.e., the first plane and the second plane are same planes, the second fuel divider 414 and the first fuel divider 408 of an embodiment in FIG. 5 are advantageously positioned in different planes i.e. the first plane is different from the second plane. In the preferred embodiment shown in FIG. 5 , inlet of the second fuel divider 414 and one outlet of the first fuel divider 408 are connected substantially at 90 degrees angle.
  • dual fuel delivery system 400 has advantageously a more compact size, which reduces a need for a large space inside the gas turbine 100 .
  • the two planes, the first plane and the second plane may be inclined to each other at an angle >10 degrees, preferably greater of 50 degrees up to 90 degrees.
  • Another advantage of having fuel dividers 408 and 414 in different planes instead in one plane is an additional degree of flexibility to compensate for thermal extension and/or vibrations in different directions.
  • Other designs, depending of the geometry of the gas turbine, are possible, without departing from the main concept of the invention.
  • a connection between the main fuel oil conduit 406 and the first fuel oil divider 412 may have a horizontal sliding guide 504 .
  • a connection between the first fuel oil divider 412 and the second fuel oil divider 414 may have a vertical sliding guide 502 .
  • the use of the sliding guides 502 and 504 helps to guide the relative movements of the metal hoses 426 inside a gas turbine engine.
  • FIG. 5 shows also a fuel manifold 506 connected to the inlet of the main fuel line 402 .
  • the manifold 506 is used to supply the fuel gas and the oil gas to the main fuel line 402 via fuel oil inlet 508 and fuel gas inlet 510 .
  • the inlets 508 and 510 are in general connected to the external fuel gas and fuel oil supply (not shown).
  • FIG. 6 shows perspective view of the dual fuel delivery system 400 according to another preferred embodiment of the present invention.
  • FIG. 6 shows only external part of the system 400 , without showing internal gas oil conduits and dividers.
  • the system 400 comprises also an injection head 602 .
  • the role of the injection head 602 is to inject the fuel into a burner.
  • the injection head 602 comprises one or more injection nozzles 604 adapted to inject the fuel oil and/or the fuel gas.
  • the injection head 602 is connected to the second fuel dividers 414 .
  • the dual fuel from the manifold 506 may be guided to the nozzles 604 .
  • the injection head 602 comprises plurality of fuel injection sections 606 . In the embodiment shown in FIG.
  • the injection section 606 there are 4 fuel injection sections 606 , each section having nine nozzles 604 .
  • One example of the injection section 606 is described in patent application EP 2496883A2.
  • the injection section 606 has streamlined body defined by two lateral surfaces joined in a smooth round transition at a leading edge and ending at a small radius/sharp angle at a trailing edge. Upstream of the trailing edge vortex generators may be located.
  • the nozzles 604 are located on the trailing edge of the streamlined body of the injection sections 606 .
  • FIG. 7 shows in more detail a connection between the injection head 602 and the outlets of the dividers 414 , showing that every injection section 606 is connected to one outlet of the dividers 414 .
  • FIG. 8 shows a rectangular type burner 800 adapted to be used with the dual fuel delivery system 400 according to the invention. As shown, the burner 800 is adapted to receive the injection head 602 .
  • gas turbine 100 preferably comprises a can combustor 902 , a cooling air housing 904 , and a burner 800 adapted to receive the injection head 602 .
  • gas turbine 100 preferably comprises a can combustor 902 , a cooling air housing 904 , and a burner 800 adapted to receive the injection head 602 .
  • the inlet of the main fuel line 402 is positioned outside the can housing 902 ; the outlet of the main fuel line 402 and the inlet to the first fuel divider 408 are positioned between the can housing 902 and the cooling air housing 904 .
  • the outlets of the second fuel dividers are positioned inside the burner 800 .
  • FIG. 9 also illustrates the method for delivering dual fuel, the fuel oil 112 and the fuel gas 114 , to the injection head inside the burner 800 of the gas turbine 100 comprising the dual fuel delivery system 400 .
  • the fuel oil 112 and/or the fuel gas 114 are supplied to the main fuel line 402 , and then they are divided in the fuel divider 408 and fuel dividers 414 , and guided to the burner 800 where the fuel is mixed with compressed air and burned.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US15/079,560 2015-03-27 2016-03-24 Integrated dual fuel delivery system Active 2037-03-19 US10385780B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP15161382 2015-03-27
EP15161382.5 2015-03-27
EP15161382.5A EP3073198B1 (en) 2015-03-27 2015-03-27 Integrated dual fuel delivery system

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US20160281606A1 US20160281606A1 (en) 2016-09-29
US10385780B2 true US10385780B2 (en) 2019-08-20

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US (1) US10385780B2 (zh)
EP (1) EP3073198B1 (zh)
JP (1) JP2016191543A (zh)
KR (1) KR20160115834A (zh)
CN (1) CN106050431B (zh)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3361159B1 (en) 2017-02-13 2019-09-18 Ansaldo Energia Switzerland AG Method for manufacturing a burner assembly for a gas turbine combustor and burner assembly for a gas turbine combustor
EP3361161B1 (en) * 2017-02-13 2023-06-07 Ansaldo Energia Switzerland AG Burner assembly for a combustor of a gas turbine power plant and combustor comprising said burner assembly
US11242806B2 (en) * 2017-11-20 2022-02-08 Power Systems Mfg., Llc Method of controlling fuel injection in a reheat combustor for a combustor unit of a gas turbine
CN108662612B (zh) * 2018-04-13 2020-05-22 清华大学 一种多沸点燃料混合燃烧装置及其点火燃烧方法
RU206191U1 (ru) * 2021-04-20 2021-08-30 Александра Сергеевна Бадмаева Печное газораспределительное устройство
CN113700559B (zh) * 2021-09-15 2024-07-02 中国船舶重工集团公司第七0三研究所 一种海上设施的双燃料燃气轮机发电机组
KR102583223B1 (ko) * 2022-01-28 2023-09-25 두산에너빌리티 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스터빈

Citations (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4201046A (en) 1977-12-27 1980-05-06 United Technologies Corporation Burner nozzle assembly for gas turbine engine
CA1170844A (en) 1982-06-25 1984-07-17 Carl E. Pearson Gas turbine fuel system
US4463568A (en) * 1981-07-28 1984-08-07 Rolls-Royce Limited Fuel injector for gas turbine engines
US4467610A (en) 1981-04-17 1984-08-28 General Electric Company Gas turbine fuel system
US4763481A (en) * 1985-06-07 1988-08-16 Ruston Gas Turbines Limited Combustor for gas turbine engine
US4833878A (en) * 1987-04-09 1989-05-30 Solar Turbines Incorporated Wide range gaseous fuel combustion system for gas turbine engines
US5133192A (en) * 1989-08-31 1992-07-28 Rolls-Royce Plc Fuel vaporizer
US5361578A (en) 1992-08-21 1994-11-08 Westinghouse Electric Corporation Gas turbine dual fuel nozzle assembly with steam injection capability
US5408830A (en) * 1994-02-10 1995-04-25 General Electric Company Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines
CN1139735A (zh) 1995-07-03 1997-01-08 Abb管理有限公司 环形燃烧室燃气轮机的燃料输入管道
US5680766A (en) * 1996-01-02 1997-10-28 General Electric Company Dual fuel mixer for gas turbine combustor
US5778676A (en) * 1996-01-02 1998-07-14 General Electric Company Dual fuel mixer for gas turbine combustor
US20090277182A1 (en) 2008-05-09 2009-11-12 Alstom Technology Ltd Fuel lance
GB2462915A (en) 2008-08-28 2010-03-03 Delavan Inc Fuel distribution manifold system for gas turbine engines
US20100077760A1 (en) * 2008-09-26 2010-04-01 Siemens Energy, Inc. Flex-Fuel Injector for Gas Turbines
EP2189720A1 (de) 2008-11-21 2010-05-26 Siemens Aktiengesellschaft Brenneranordnung
US20100242482A1 (en) 2009-03-30 2010-09-30 General Electric Company Method and system for reducing the level of emissions generated by a system
US20120055162A1 (en) * 2010-06-23 2012-03-08 Alstom Technology Ltd Lance of a burner
US20130074946A1 (en) 2011-09-23 2013-03-28 Siemens Energy, Inc. CAST MANIFOLD FOR DRY LOW NOx GAS TURBINE ENGINE
US20130291547A1 (en) 2012-05-02 2013-11-07 Mitsubishi Heavy Industries, Ltd. Purge method and purge unit for gas turbine combustor

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5167662B2 (ja) * 2007-03-19 2013-03-21 株式会社リコー ワークフロー管理システム
WO2011054771A2 (en) 2009-11-07 2011-05-12 Alstom Technology Ltd Premixed burner for a gas turbine combustor

Patent Citations (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4201046A (en) 1977-12-27 1980-05-06 United Technologies Corporation Burner nozzle assembly for gas turbine engine
US4467610A (en) 1981-04-17 1984-08-28 General Electric Company Gas turbine fuel system
US4463568A (en) * 1981-07-28 1984-08-07 Rolls-Royce Limited Fuel injector for gas turbine engines
CA1170844A (en) 1982-06-25 1984-07-17 Carl E. Pearson Gas turbine fuel system
US4763481A (en) * 1985-06-07 1988-08-16 Ruston Gas Turbines Limited Combustor for gas turbine engine
US4833878A (en) * 1987-04-09 1989-05-30 Solar Turbines Incorporated Wide range gaseous fuel combustion system for gas turbine engines
US5133192A (en) * 1989-08-31 1992-07-28 Rolls-Royce Plc Fuel vaporizer
US5361578A (en) 1992-08-21 1994-11-08 Westinghouse Electric Corporation Gas turbine dual fuel nozzle assembly with steam injection capability
US5408830A (en) * 1994-02-10 1995-04-25 General Electric Company Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines
US5765366A (en) 1995-07-03 1998-06-16 Asea Brown Boveri Ag Fuel feed for gas turbines having an annular combustion chamber
CN1139735A (zh) 1995-07-03 1997-01-08 Abb管理有限公司 环形燃烧室燃气轮机的燃料输入管道
US5778676A (en) * 1996-01-02 1998-07-14 General Electric Company Dual fuel mixer for gas turbine combustor
US5680766A (en) * 1996-01-02 1997-10-28 General Electric Company Dual fuel mixer for gas turbine combustor
US20090277182A1 (en) 2008-05-09 2009-11-12 Alstom Technology Ltd Fuel lance
GB2462915A (en) 2008-08-28 2010-03-03 Delavan Inc Fuel distribution manifold system for gas turbine engines
US20100050645A1 (en) 2008-08-28 2010-03-04 Delavan Inc Fuel distribution manifold system for gas turbine engines
US20100077760A1 (en) * 2008-09-26 2010-04-01 Siemens Energy, Inc. Flex-Fuel Injector for Gas Turbines
EP2189720A1 (de) 2008-11-21 2010-05-26 Siemens Aktiengesellschaft Brenneranordnung
US20100242482A1 (en) 2009-03-30 2010-09-30 General Electric Company Method and system for reducing the level of emissions generated by a system
EP2236935A2 (en) 2009-03-30 2010-10-06 General Electric Company Method And System For Reducing The Level Of Emissions Generated By A System
US20120055162A1 (en) * 2010-06-23 2012-03-08 Alstom Technology Ltd Lance of a burner
US20130074946A1 (en) 2011-09-23 2013-03-28 Siemens Energy, Inc. CAST MANIFOLD FOR DRY LOW NOx GAS TURBINE ENGINE
CN103930724A (zh) 2011-09-23 2014-07-16 西门子公司 用于双燃料双级干式低nox燃气涡轮发动机的铸造歧管
US9163841B2 (en) 2011-09-23 2015-10-20 Siemens Aktiengesellschaft Cast manifold for dry low NOx gas turbine engine
US20130291547A1 (en) 2012-05-02 2013-11-07 Mitsubishi Heavy Industries, Ltd. Purge method and purge unit for gas turbine combustor

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
Office Action (Communication) dated Oct. 25, 2018, by the European Patent Office in corresponding European Patent Application No. 15161382.5. (5 pages).
Office Action and Search Report dated Dec. 27, 2018, by the Chinese Patent Office in corresponding Chinese Patent Application No. 201610321294.7, and an English Translation of the Office Action. (9 pages).
Search Report dated Aug. 27, 2015, by the European Patent Office for Application No. 15161427.
Search Report dated Oct. 9, 2015, by the European Patent Office for Application No. 15161382.

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KR20160115834A (ko) 2016-10-06
CN106050431A (zh) 2016-10-26
EP3073198A1 (en) 2016-09-28
JP2016191543A (ja) 2016-11-10
US20160281606A1 (en) 2016-09-29
EP3073198B1 (en) 2019-12-25

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