US20110091829A1 - Multi-fuel combustion system - Google Patents

Multi-fuel combustion system Download PDF

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Publication number
US20110091829A1
US20110091829A1 US12/581,978 US58197809A US2011091829A1 US 20110091829 A1 US20110091829 A1 US 20110091829A1 US 58197809 A US58197809 A US 58197809A US 2011091829 A1 US2011091829 A1 US 2011091829A1
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US
United States
Prior art keywords
fuel
combustor basket
type
combustion system
conduit
Prior art date
Legal status (The legal status 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 status listed.)
Abandoned
Application number
US12/581,978
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English (en)
Inventor
Vinayak Barve
Timothy A. Fox
Jianfan Wu
Ulrich Wörz
Jaap van Kampen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
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Siemens AG
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 AG filed Critical Siemens AG
Priority to US12/581,978 priority Critical patent/US20110091829A1/en
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FOX, TIMOTHY A., WOERZ, ULRICH, WU, JIANFAN, BARVE, VINAYAK, VAN KAMPEN, JAAP
Priority to JP2012534677A priority patent/JP5657681B2/ja
Priority to PCT/EP2010/065764 priority patent/WO2011048123A2/en
Priority to CN201080046150.6A priority patent/CN102844622B/zh
Priority to EP10776606A priority patent/EP2491305A2/en
Priority to US13/502,555 priority patent/US20120260666A1/en
Publication of US20110091829A1 publication Critical patent/US20110091829A1/en
Priority to JP2014196783A priority patent/JP5921630B2/ja
Abandoned legal-status Critical Current

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Classifications

    • 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
    • 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
    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
    • Y02E20/18—Integrated gasification combined cycle [IGCC], e.g. combined with carbon capture and storage [CCS]

Definitions

  • the present invention lies in the field of combustion turbines in particular for generating electrical energy and more particularly, to combustor baskets employed therein.
  • Syngas typically has a significantly lower calorific value as compared to conventional natural gas fuels.
  • CO 2 carbon-dioxide
  • the IGCC concept with pre-combustion CO 2 capture is one of the most cost-effective ways to produce electricity and avoid the emission of CO 2 in the future.
  • the economical potential of the IGCC plant with CO 2 capture can increase even further when natural gas prices rise faster than expected or with increased carbon tax regulation.
  • the syngas fuel composition depends on the type of gasifier used and on whether or not the CO is separated from the fuel. Besides syngas fuels, the combustion system might run on a second conventional fuel for backup and start up. The ideal possibility is to have all the different types of fuels combusted in a stable way by one combustion system. To increase the efficiency and compensate for the efficiency loss due to the gasifier and CO 2 separation techniques, the trend will be to increase pressure and turbine inlet temperatures, even beyond values where currently natural gas experience is available. With these increasing pressures and temperatures, it becomes even more important to design a combustion system that is able to combust the syngas and hydrogen fuel, as danger for burner overheating and thermo acoustic excitation typically increases with pressure and temperature.
  • an embodiment herein includes a multi-fuel combustion system comprising: a combustor basket adapted to combust at least two type of fuels, said combustor basket having a circumferential wall comprising a plurality of openings; a first conduit adapted to provide a first type of fuel directly to the combustor basket; a second conduit adapted to provide a second type of fuel directly to the combustor basket; and a third conduit adapted to inject at least one of the first type of fuel and the second type of fuel trough the openings into the combustor basket.
  • another embodiment herein includes a method of operating a multi-fuel combustion system comprising a first phase and a second phase, wherein the first phase comprises: providing ignition to a combustor basket to ignite a first type of fuel, where the first type of fuel is supplied to the combustor basket through a first conduit; supplying steam to the first conduit in addition to the first type of fuel and supplying steam to the second conduit after the ignition; and wherein the second phase comprises: supplying a second type of fuel to the combustor basket after ignition of the first fuel through the second conduit, while stopping the supply of the first fuel.
  • FIG. 1 illustrates a longitudinal cross-section of the multi-fuel combustion system
  • FIG. 2 shows fuel injector holes at the region of nozzle of the first and the second conduits
  • FIG. 3 shows the fuel injector holes of the first conduit based on a preferred embodiment of the invention
  • FIG. 4 illustrates a first embodiment of cross section of the combustor basket taken along the plane 2 - 2 a of FIG. 1 ,
  • FIG. 5 illustrates a second embodiment of cross section of the combustor basket taken along the plane 2 - 2 a of FIG. 1 ,
  • FIG. 6 illustrates a third embodiment of cross section of the combustor basket taken along the plane 2 - 2 a of FIG. 1 ,
  • FIG. 7 illustrates the arrangement of the wall of the combustor basket
  • FIG. 8 illustrates the rib structure of the cylindrical region of the combustor basket
  • FIG. 9 illustrates a transition and a flow conditioner arrangement according to an embodiment of the invention.
  • a combustion turbine comprises three sections: a compressor section, a combustor section having a typical combustor basket and a turbine section. Air drawn into the compressor section is compressed. The compressed air from the compressor section flows through the combustor section where the temperature of the air mass is further increased after combustion of a fuel. From the combustor section the hot pressurized gas flow into the turbine section where the energy of the expanding gases is transformed into rotational motion of a turbine rotor that drives an electric generator.
  • the burner should be able to handle large fuel mass flows and the fuel passages consequently need to have a large capacity. A too small capacity results in a high fuel pressure drop. Due to the large fuel mass flow involved, a high pressure drop has a much larger impact on the total efficiency of the engine as compared to a typical natural gas fired engine.
  • FIG. 1 illustrates a cross-sectional view of the multi-fuel combustion system 10 according to one embodiment of the invention.
  • a multi-fuel combustion system 10 comprises a combustor basket 12 .
  • the wall 16 of the combustor basket 12 is made of multiple cylindrical regions 14 arranged to overlap each other at the transition and extends from an upstream end 20 to a downstream end 22 of the combustor basket.
  • the upstream end 20 of the combustor basket is close to the region, where the fuel conduits generally supply the fuels for the combustion and the down stream end is the region, where the gas after combustion flows out to of the combustor basket to a turbine section.
  • the combustion system 10 is designed to combust at least two type of fuels, for example natural gas and syngas. The types of fuels that could be used are not restricted to natural gas and syngas and hence the combustion system 10 could use other fuels for combustion.
  • FIG. 1 further shows a first conduit 24 adapted to provide a first type of fuel, for example natural gas, directly to the combustor basket 12 and the second conduit 26 is adapted to provide a second type of fuel, for example syngas directly to the combustor basket 12 . Also there is at last one third conduit 25 adapted to inject at least one of the first type of fuel and the second type of fuel through one or multiple openings 18 into the combustor basket 12 . There could be more than one conduit to provide each type of fuel to the combustor basket based on the design and requirement. For example, there could be multiple third conduits 25 to supply the fuel through multiple openings 18 in the combustor basket 12 .
  • each of the conduits is adapted to handle a different fuel. Even the conduits could handle multiple fuels at the same point of time.
  • the second conduit 26 is positioned to encircle the first conduit 24 or concentrically arranged for effective delivery of the fuels.
  • the first conduit 24 is positioned coaxially, and internally, of a larger diameter second conduit 26 . Since the diameter of the second conduit 26 is greater that the first conduit 24 , the said second conduit 26 can handle low calorific value fuels of larger volumes since large fuel mass flows is needed to achieve a certain thermal power input.
  • the third conduit 25 is adapted to inject at least one of the first type of fuel and the second type of fuel into a compressor discharge air that flow through at least one of the openings 18 associated with at least one of the cylindrical regions 14 .
  • the third conduit 25 has a fuel injector nozzle 27 at the end having 1 to 5 injector holes that are aimed at an angle of 0 to 90° relative to a centerline of the opening 18 .
  • the first conduits 24 and the second conduit 26 under consideration consist of concentric circles of circular holes at the region of nozzle 28 of the conduits which acts as injectors for the fuels.
  • the nozzle 28 helps to inject the respective fuels directly into the combustor basket 12 and is positioned at the upstream end 20 of the combustor basket 12 .
  • FIG. 2 shows explicitly these two rows of concentric holes at the region of nozzle 28 .
  • Each circle of rows is associated to a conduit.
  • the inner row of holes 21 corresponds to the first conduit 24 and the outer row of holes 23 corresponds to the second conduit 26 .
  • the number of injectors in each conduit can vary, for example between 8 to 18 holes, but is not restricted to this numbers.
  • a preferred embodiment having 14 injectors for both conduits is shown in FIG. 2 .
  • the holes can be clocked relative to each other or can be inline.
  • the holes in the region of nozzle 28 of the first conduit 24 comprises multiple holes positioned at, at least two different radial distances from the center of the nozzle for injecting a fuel flow into a region of combustion in the combustor basket 12 .
  • This nozzle design promotes a greater amount of fuel flow towards the center of the nozzle, which cools the nozzle in a cost effective and simple manner. Most importantly the hole arrangement maintains the aerodynamic performance of the nozzle.
  • FIG. 3 shows such a nozzle 30 , of such a type used by the first conduit 24 to inject the fuel to the combustor basket 12 .
  • the first set of holes 32 and the second set of holes 34 are arranged at a first radial distance 31 and at a second radial distance 33 respectively from the center 36 of the nozzle.
  • the circumferential wall 16 of the combustor basket 12 comprises multiple openings 18 .
  • At least two of the cylindrical regions 14 a and 14 b nearer to the upstream end 20 of the combustor basket 12 further comprise multiple openings 18 distributed along the circumference of the respective cylindrical regions. This multiple openings 18 allow a compressor discharge air from a compressor stage to flow towards a region of combustion in the combustor basket.
  • at least one of the cylindrical region near to the downstream end 22 of the combustor basket 10 may also comprise plurality of openings 18 distributed along the circumference of the cylindrical region to allow the compressor discharge air to flow towards a region of combustion in the combustor basket 12 .
  • FIG. 4 illustrates a first embodiment 40 of cross section of the combustor basket 12 taken along the plane 2 - 2 a of FIG. 1 .
  • the number of openings in the individual cylindrical region 14 varies between 5 and 9 based on the embodiments.
  • FIG. 4 shows 6 numbers of openings 18 in the circular region 14 of the combustor basket 12 .
  • FIG. 5 illustrates a second embodiment 50 of cross section of the combustor basket taken along the plane 2 - 2 a of FIG. 1 .
  • FIG. 5 shows 7 numbers of openings 18 in the circular region 14 of the combustor basket 12 .
  • FIG. 6 illustrates a third embodiment 60 of cross section of the combustor basket 12 taken along the plane 2 - 2 a of FIG. 1 .
  • FIG. 6 shows 9 numbers of openings 18 in the circular region 14 of the combustor basket 12 .
  • These openings in the combustor basket are like scoops, especially radial scoops through which compressor discharge air is injected in the combustor basket 12 .
  • the openings are alternatively referred to as scoops in few places in the description for convenience.
  • the length of the scoops is half the diameter of the scoop.
  • FIG. 6 shows an opening 18 , having a length 43 and a diameter 41 .
  • This length is oriented to the interior region of the combustor basket 12 . This length helps to lead the air further into the combustion region.
  • the scoops deliver air flow with greater penetration into the fuel stream, achieving improved heating efficiency and more complete combustion.
  • the openings 18 are equally distributed along the circumference of the cylindrical region 14 . Odd numbers of openings are beneficial for wall temperatures and helps against thermo-acoustic problems, since they provide a rotational asymmetrical configuration.
  • the scoops can be circular or oval in cross-section. When the scoops are oval, the smallest dimension of the oval shape lies in the direction of the basket centerline.
  • the scoops can have an angle of 0-45° relative to the radial direction, from the basket centerline and aiming downstream when angled.
  • few or all the scoops in a cylindrical region can have an angle of 15°
  • few or all the scoops in another cylindrical region can have an angle of 0°, i.e. aimed radial towards the center line.
  • the scoops can be directed against the flow of thrust of the combustor system with an angle up to 15° relative to radial direction.
  • the downstream edges of the scoops are cut-off at an angle between 0-60° relative to the centerline of the combustor basket. This is basically to avoid damages caused by the recirculation of hot air to the scoops.
  • the combustion system 10 further comprises a cover plate 29 coupled to the combustor basket 12 and the first, second and third conduits. This enables the combustor basket and the conduits to be attached to a casing.
  • FIG. 7 illustrates the arrangement 70 of the wall 16 of the combustor basket.
  • the wall 16 of the combustor basket 12 is made of a plurality of cylindrical regions 14 arranged to overlap each other at the transition.
  • the individual cylindrical region 14 comprises an outer surface 72 , said outer surface 72 is provided with a rib structure 82 as shown in FIG. 8 .
  • the outer surface 72 is covered substantially by a perforated layer 74 adapted to provide an air flow for cooling the wall 16 .
  • the wall 16 of the combustor basket 12 is cooled by convection and effusion cooling.
  • plate fin design as shown in FIG. 7 is used. These plate fins consist of two liners.
  • the inner liner which is basically the cylindrical region is provided with the cooling rib structure 82 in the outer surface 72 to increase the cooling surface.
  • the outer liner is the perforated layer 74 . When the cooling air exits the plate fin, it serves as effusion cooling air.
  • the multi-fuel combustion system 10 further comprises a flow conditioner 45 positioned to encircle the combustor basket 12 and having a conical section 46 and a cylindrical section 47 having plurality of holes 48 adapted to allow the compressor discharge air to flow towards a region of combustion in the combustor basket 12 .
  • the flow conditioner 45 is used to achieve the pressure drop required for cooling and to provide a uniform air flow towards the region of combustion in the combustor basket 12 .
  • Holes 48 in both the cylindrical section 47 and the conical section 46 are used as flow passage for air.
  • a gap 92 exists between the transition 94 and the end 96 of the conical section 46 of the flow conditioner 45 .
  • the flow conditioner 45 slightly overlaps the transition 94 . In this way thermal expansion does not affect the flow area of the gap 92 .
  • the conical section 46 and a cylindrical section 47 is connected together by a flange or could be welded together.
  • the multi-fuel combustion system 1 of FIG. 1 further comprises an exit cone 35 at the downstream end 22 of the combustor basket 12 having multiple slots 37 aligned to the plurality of openings 18 associated with at least one of the cylindrical regions 14 .
  • This exit cone 35 is intended to improve the mixing between the hot combustion gasses and the cold air flow coming out of a spring-clip passage 39 . The improved mixing between these flows lead to better CO emissions.
  • the exit cone slots 37 aligned with the scoops 18 prevent overheating of the exit cone 35 .
  • the method of operating the multi-fuel combustion system 10 is now described.
  • the operation could be divided into two main phases a first phase and a second phase.
  • a first phase an ignition is provided to a combustor basket by an ignition coil to ignite a first type of fuel, for example natural gas supplied to the combustor basket 12 through the first conduit 24 .
  • the method also involves supplying steam to the first conduit 24 in addition to the first type of fuel and supplying steam to the second conduit 26 after the ignition. Steam is provided to the second conduit 26 at a time earlier than the steam provided to the first conduit 24 .
  • the method further involves supplying a medium, for example an inert gas, nitrogen, steam or seal air to the second conduit 26 during the first phase for stabilizing the combustion system 10 for any pressure difference in the combustor basket 12 .
  • a medium for example an inert gas, nitrogen, steam or seal air
  • the combustion system or the turbine comprises a plurality of combustor baskets, and while in operation there could be pressure differences that could be built up between these combustor baskets.
  • the supply of the medium also takes care of this pressure difference in the combustor basket due to this type of arrangement.
  • the supply of the medium in the second conduit 26 is shut off once the steam supply is stabilized in the first conduit 24 and the second conduit 26 during the first stage of operation.
  • a second type of fuel for example syngas is supplied to the combustor basket through the second conduit 26 , while stopping the supply of the first fuel.
  • the method further comprises supplying a portion of the second type of fuel to the combustor basket 12 through the first conduit 24 during the second phase.
  • the steam is continuously supplied in the first conduit 24 from the first phase until the beginning of supplying the portion of the second type of fuel through the first conduit 24 during the second phase.
  • the third conduit 25 may also be used to supply any one of the first or second type of fuel for enabling an effective and more complete combustion by introducing the said fuels through the openings 18 if required. This further helps in reducing NOx emissions.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
US12/581,978 2009-10-20 2009-10-20 Multi-fuel combustion system Abandoned US20110091829A1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US12/581,978 US20110091829A1 (en) 2009-10-20 2009-10-20 Multi-fuel combustion system
JP2012534677A JP5657681B2 (ja) 2009-10-20 2010-10-20 混焼システム
PCT/EP2010/065764 WO2011048123A2 (en) 2009-10-20 2010-10-20 A multi-fuel combustion system
CN201080046150.6A CN102844622B (zh) 2009-10-20 2010-10-20 一种多燃料燃烧系统
EP10776606A EP2491305A2 (en) 2009-10-20 2010-10-20 A multi-fuel combustion system
US13/502,555 US20120260666A1 (en) 2009-10-20 2010-10-20 Multi-fuel combustion system
JP2014196783A JP5921630B2 (ja) 2009-10-20 2014-09-26 混焼システムを運転する方法

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US12/581,978 US20110091829A1 (en) 2009-10-20 2009-10-20 Multi-fuel combustion system

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US13/502,555 Division US20120260666A1 (en) 2009-10-20 2010-10-20 Multi-fuel combustion system

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US13/502,555 Abandoned US20120260666A1 (en) 2009-10-20 2010-10-20 Multi-fuel combustion system

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EP (1) EP2491305A2 (ja)
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WO (1) WO2011048123A2 (ja)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140137535A1 (en) * 2012-11-20 2014-05-22 General Electric Company Clocked combustor can array
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
US20150362194A1 (en) * 2014-06-12 2015-12-17 Kawasaki Jukogyo Kabushiki Kaisha Multifuel gas turbine combustor
CN105276619A (zh) * 2014-06-12 2016-01-27 川崎重工业株式会社 适合多种燃料的燃气轮机燃烧器
WO2016039745A1 (en) * 2014-09-11 2016-03-17 Siemens Energy, Inc. Syngas burner system for a gas turbine engine
EP3008391A4 (en) * 2013-06-11 2016-07-06 United Technologies Corp AXIS SHELTER COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
EP2933561A4 (en) * 2012-12-13 2016-08-24 Kawasaki Heavy Ind Ltd MULTI-FACTORY GAS TURBINE CHAMBER
WO2017025295A1 (de) * 2015-08-10 2017-02-16 Siemens Aktiengesellschaft Brennerlanze für einen pilotbrenner
US20170211805A1 (en) * 2014-08-14 2017-07-27 Siemens Aktiengesellschaft Multi-functional fuel nozzle with an atomizer array
US10359194B2 (en) 2014-08-26 2019-07-23 Siemens Energy, Inc. Film cooling hole arrangement for acoustic resonators in gas turbine engines
US10443855B2 (en) 2014-10-23 2019-10-15 Siemens Aktiengesellschaft Flexible fuel combustion system for turbine engines

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140083111A1 (en) * 2012-09-25 2014-03-27 United Technologies Corporation Gas turbine asymmetric fuel nozzle combustor
JP6010489B2 (ja) * 2013-03-12 2016-10-19 三菱日立パワーシステムズ株式会社 熱電可変型コジェネレーションシステム

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3044263A (en) * 1959-05-21 1962-07-17 Dresser Ind Combustor with unitary liner
US3650106A (en) * 1968-10-18 1972-03-21 Bennes Marrel Sa Combustion chamber for gas turbine
US5584684A (en) * 1994-05-11 1996-12-17 Abb Management Ag Combustion process for atmospheric combustion systems
US5758504A (en) * 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner
US6201029B1 (en) * 1996-02-13 2001-03-13 Marathon Oil Company Staged combustion of a low heating value fuel gas for driving a gas turbine
US7908864B2 (en) * 2006-10-06 2011-03-22 General Electric Company Combustor nozzle for a fuel-flexible combustion system

Family Cites Families (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8008A (en) * 1851-04-01 hollingsworth
US3015A (en) * 1843-03-21 Improvement in gilding, silvering
US4236378A (en) * 1978-03-01 1980-12-02 General Electric Company Sectoral combustor for burning low-BTU fuel gas
JPS58137234U (ja) * 1982-03-11 1983-09-14 石川島播磨重工業株式会社 燃焼器用噴射弁
JPH03195821A (ja) * 1989-12-26 1991-08-27 Hitachi Ltd ガスタービン燃焼器
US5259184A (en) * 1992-03-30 1993-11-09 General Electric Company Dry low NOx single stage dual mode combustor construction for a gas turbine
JPH0722259U (ja) * 1993-09-03 1995-04-21 株式会社東芝 燃焼器ライナ構造体
US5564271A (en) * 1994-06-24 1996-10-15 United Technologies Corporation Pressure vessel fuel nozzle support for an industrial gas turbine engine
GB2297151B (en) * 1995-01-13 1998-04-22 Europ Gas Turbines Ltd Fuel injector arrangement for gas-or liquid-fuelled turbine
JP3110300B2 (ja) * 1995-11-27 2000-11-20 三菱重工業株式会社 燃焼器
JPH1130131A (ja) * 1997-07-09 1999-02-02 Hitachi Ltd ガス化複合発電プラント及びその運転方法
JP2000097435A (ja) * 1998-09-25 2000-04-04 Hitachi Ltd ガスタービン燃焼器
JP4094196B2 (ja) * 2000-01-07 2008-06-04 株式会社東芝 ガスタービン燃料切替制御装置
JP2002162036A (ja) * 2000-11-22 2002-06-07 Mitsubishi Heavy Ind Ltd 燃焼器
JP3872960B2 (ja) * 2001-02-28 2007-01-24 株式会社日立製作所 ガスタ−ビン燃焼器
JP3915423B2 (ja) * 2001-03-29 2007-05-16 株式会社日立製作所 ガスタービン燃焼器ライナー構造とその補修方法
US20030150216A1 (en) * 2001-07-03 2003-08-14 O'beck John Timothy Gas turbine
EP1277920A1 (de) * 2001-07-19 2003-01-22 Siemens Aktiengesellschaft Verfahren zum Betrieb eines Brenners einer Gasturbine sowie Kraftwerksanlage
JP3665007B2 (ja) * 2001-10-18 2005-06-29 三菱重工業株式会社 ガスタービン燃焼器のプレートフィン構造及びガスタービン燃焼器
SE0301585D0 (sv) * 2003-05-30 2003-05-30 Euroturbine Ab Förfarande för drift av en gasturbingrupp
US6935117B2 (en) * 2003-10-23 2005-08-30 United Technologies Corporation Turbine engine fuel injector
JP4728176B2 (ja) * 2005-06-24 2011-07-20 株式会社日立製作所 バーナ、ガスタービン燃焼器及びバーナの冷却方法
WO2007113074A1 (de) * 2006-03-31 2007-10-11 Alstom Technology Ltd Brennstofflanze für eine gasturbinenanlage sowie ein verfahren zum betrieb einer brennstofflanze
ES2551506T3 (es) * 2006-06-07 2015-11-19 Alstom Technology Ltd Procedimiento para el funcionamiento de una turbina de gas y central eléctrica combinada para la realización del procedimiento
EP1998115A1 (de) * 2007-05-29 2008-12-03 Siemens Aktiengesellschaft Kühlkanal zum Kühlen einer ein Heißgas führenden Komponente
JP2011075173A (ja) * 2009-09-30 2011-04-14 Hitachi Ltd 燃焼器
US20110091824A1 (en) * 2009-10-20 2011-04-21 Vinayak Barve Method of operating a multi-fuel combustion system

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3044263A (en) * 1959-05-21 1962-07-17 Dresser Ind Combustor with unitary liner
US3650106A (en) * 1968-10-18 1972-03-21 Bennes Marrel Sa Combustion chamber for gas turbine
US5584684A (en) * 1994-05-11 1996-12-17 Abb Management Ag Combustion process for atmospheric combustion systems
US6201029B1 (en) * 1996-02-13 2001-03-13 Marathon Oil Company Staged combustion of a low heating value fuel gas for driving a gas turbine
US5758504A (en) * 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner
US7908864B2 (en) * 2006-10-06 2011-03-22 General Electric Company Combustor nozzle for a fuel-flexible combustion system

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140137535A1 (en) * 2012-11-20 2014-05-22 General Electric Company Clocked combustor can array
US9546601B2 (en) * 2012-11-20 2017-01-17 General Electric Company Clocked combustor can array
EP2933561A4 (en) * 2012-12-13 2016-08-24 Kawasaki Heavy Ind Ltd MULTI-FACTORY GAS TURBINE CHAMBER
EP3008391A4 (en) * 2013-06-11 2016-07-06 United Technologies Corp AXIS SHELTER COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
US11143407B2 (en) 2013-06-11 2021-10-12 Raytheon Technologies Corporation Combustor with axial staging for a gas turbine engine
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
US20150362194A1 (en) * 2014-06-12 2015-12-17 Kawasaki Jukogyo Kabushiki Kaisha Multifuel gas turbine combustor
CN105276619A (zh) * 2014-06-12 2016-01-27 川崎重工业株式会社 适合多种燃料的燃气轮机燃烧器
US9638423B2 (en) * 2014-06-12 2017-05-02 Kawasaki Jukogyo Kabushiki Kaisha Multifuel gas turbine combustor with fuel mixing chamber and supplemental burner
US9958152B2 (en) * 2014-08-14 2018-05-01 Siemens Aktiengesellschaft Multi-functional fuel nozzle with an atomizer array
US20170211805A1 (en) * 2014-08-14 2017-07-27 Siemens Aktiengesellschaft Multi-functional fuel nozzle with an atomizer array
US10359194B2 (en) 2014-08-26 2019-07-23 Siemens Energy, Inc. Film cooling hole arrangement for acoustic resonators in gas turbine engines
WO2016039745A1 (en) * 2014-09-11 2016-03-17 Siemens Energy, Inc. Syngas burner system for a gas turbine engine
CN106687745A (zh) * 2014-09-11 2017-05-17 西门子能源公司 用于燃气涡轮发动机的合成气燃烧器系统
US10443855B2 (en) 2014-10-23 2019-10-15 Siemens Aktiengesellschaft Flexible fuel combustion system for turbine engines
WO2017025295A1 (de) * 2015-08-10 2017-02-16 Siemens Aktiengesellschaft Brennerlanze für einen pilotbrenner

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WO2011048123A2 (en) 2011-04-28
JP5921630B2 (ja) 2016-05-24
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CN102844622A (zh) 2012-12-26
WO2011048123A3 (en) 2012-12-20

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