US20030037549A1 - Gas turbine combustor - Google Patents

Gas turbine combustor Download PDF

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Publication number
US20030037549A1
US20030037549A1 US10/198,368 US19836802A US2003037549A1 US 20030037549 A1 US20030037549 A1 US 20030037549A1 US 19836802 A US19836802 A US 19836802A US 2003037549 A1 US2003037549 A1 US 2003037549A1
Authority
US
United States
Prior art keywords
combustor
cylindrical member
mixing
mixing nozzles
combustion zone
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
US10/198,368
Other languages
English (en)
Inventor
Shigemi Mandai
Keijirou Saitoh
Katsunori Tanaka
Wataru Akizuki
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of US20030037549A1 publication Critical patent/US20030037549A1/en
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD reassignment MITSUBISHI HEAVY INDUSTRIES, LTD ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: AKIZUKI, WATARU, MANDAI, SHIGEMI, SAITOH, KEIJIROU, TANAKA, KATSUNORI
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/78—Cooling burner parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/74—Preventing flame lift-off
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • the present invention relates to a gas turbine combustor that realizes a low NOx combustion.
  • FIGS. 4 ( a ) and ( b ) schematically show a prior art gas turbine combustor, wherein FIG. 4( a ) is a longitudinal cross sectional view showing an interior of the combustor and FIG. 4( b ) is a front view of a half portion of the combustor.
  • main fuel 40 flows into eight pre-mixing nozzles 31 , that are arranged within a combustor body 36 around a central axis thereof, and is pre-mixed with air, as will be described next, to form a main pre-mixture to be supplied into a combustion zone of a combustor 33 .
  • pilot fuel 41 flows into a pilot nozzle 32 , that is arranged on the central axis of the combustor body 36 , to be jetted into the combustor 33 .
  • the pilot fuel 41 burns with the main pre-mixture there to effect a combustion.
  • a flame holding cone 34 is provided on the pilot nozzle 32 and flame of the pilot fuel 41 is maintained by a high temperature gas circulating flow 35 , that is formed by the flame holding cone 34 .
  • Such a combustor having the pre-mixing nozzles and being constructed as described above is generally known as a low NOx combustor.
  • the flame of the pilot nozzle 32 is maintained by a diffused flame, that is, the high temperature gas circulating flow 35 , formed by the flame holding cone 34 and NOx quantity generated by the pre-mixing nozzles 31 is reduced.
  • NOx quantity generated by the diffused flame of the pilot nozzle 32 cannot be suppressed and realization of a low NOx generation as a whole is limited by that extent.
  • the present invention provides means of the following (1) to (4):
  • a gas turbine combustor comprising a pilot nozzle arranged on a central axis of the combustor and a plurality of pre-mixing nozzles arranged around the pilot nozzle, characterized in that a diameter of a combustion zone of the combustor is set such that, where an area is taken on a radial directional plane of the combustor, the area inside of the combustion zone and outside of a pitch circle that is defined as a circle on which all central axes of the plurality of pre-mixing nozzles are arranged, less the area taken by the plurality of pre-mixing nozzles outside of the pitch circle, is a half or more of the area of all of-the plurality of pre-mixing nozzles.
  • each of the plurality of pre-mixing nozzles has its front end projected beyond a base plate that supports the pre-mixing nozzle and a projecting distance of such projected front end is set to one third or more of an outer diameter of the pre-mixing nozzle.
  • each of the plurality of pre-mixing nozzles has its front portion made in a double structure having inner and outer members with a predetermined gap being maintained between the inner and outer members and air is flowable in the gap.
  • a gas turbine combustor as mentioned in the means (1) above characterized in that a combustor body as an outer casing of the combustor comprises therein an inner cylindrical member and an outer cylindrical member, the inner cylindrical member is arranged surrounding the plurality of pre-mixing nozzles and the outer cylindrical member has its inner diameter made larger than an outer diameter of the inner cylindrical member and is arranged surrounding a front end portion of the inner cylindrical member and extending downstream of the inner cylindrical member so as to cover the combustion zone to thereby enable to enlarge the diameter of the combustion zone beyond an inner diameter of the inner cylindrical member.
  • the diameter of the combustion zone in which a high temperature combustion gas is generated is set such that the cross sectional area inside of the combustion zone and outside of the pitch circle, less the cross sectional area of the pre-mixing nozzles outside of the pitch circle, is a half or more of the cross sectional area of all the pre-mixing nozzles.
  • an inner circulating flow of a high temperature gas generated of the pilot fuel is formed in the central space portion of the combustion zone in front of the pilot nozzle by a flame holding cone.
  • each of the pre-mixing nozzles has its front end projected beyond the base plate so that the base plate may not be directly exposed to the high temperature gas circulating flows. Thereby, the base plate is prevented from being overheated and the effect of the means (1) of the present invention can be realized more securely.
  • each of the pre-mixing nozzles has its front portion made in the double structure having the predetermined gap therein and air is flowable in the gap for cooling the pre-mixing nozzle.
  • the pre-mixing nozzle is prevented from being overheated and the effect of the means (1) of the present invention is further ensured.
  • the combustor body as the outer casing of the combustor comprises therein the inner cylindrical member and the outer cylindrical member.
  • the outer cylindrical member has its inner diameter made larger than the outer diameter of the inner cylindrical member.
  • FIGS. 1 ( a ) and ( b ) schematically show a gas turbine combustor of an embodiment according to the present invention, wherein FIG. 1( a ) is a longitudinal cross sectional view showing an interior of the combustor and FIG. 1( b ) is a front view of a half portion of the combustor.
  • FIG. 2 is an enlarged longitudinal cross sectional view of one of pre-mixing nozzles.
  • FIG. 3 is the same view as FIG. 1( a ) in which a hatched portion is added.
  • FIGS. 4 ( a ) and ( b ) schematically show a prior art gas turbine combustor, wherein FIG. 4( a ) is a longitudinal cross sectional view showing an interior of the combustor and FIG. 4( b ) is a front view of a half portion of the combustor.
  • FIGS. 1 ( a ) and ( b ) schematically show a gas turbine combustor of the embodiment, wherein FIG. 1( a ) is a longitudinal cross sectional view showing an interior of the combustor and FIG. 1( b ) is a front view of a half portion of the combustor.
  • numeral 10 designates a combustor body as an outer casing of the combustor and eight pre-mixing nozzles 11 are provided therein being connected to each other around a central axis of the combustor body 10 .
  • the pre-mixing nozzles 11 are constructed so as to have their front ends projected beyond a base plate 17 , that will be described later.
  • Numeral 12 designates a pilot nozzle, that is arranged on the central axis of the combustor body 10 .
  • Numeral 13 designates a combustor, that includes the combustor body 10 and other components arranged therein.
  • the combustor body 10 comprises therein an inner cylindrical member 13 a and an outer cylindrical member 13 b.
  • the outer cylindrical member 13 b has its inner diameter made larger than an outer diameter of the inner cylindrical member 13 a as well as larger than an outer diameter of a cylindrical member of the prior art combustor.
  • the outer cylindrical member 13 b is arranged surrounding a front end portion of the inner cylindrical member 13 a and extending downstream of the inner cylindrical member 13 a so as to cover a combustion zone of the combustor 13 .
  • Numeral 14 designates a flame holding cone, that has its front end portion eliminated to be made shorter than the prior art flame holding cone.
  • Numeral 17 designates the base plate, that is a member supporting the eight pre-mixing nozzles 11 to an inner circumferential wall surface of the inner cylindrical member 13 a.
  • FIG. 2 is an enlarged longitudinal cross sectional view of one of the pre-mixing nozzles 11 .
  • the pre-mixing nozzle 11 has its front portion made in a double structure having a pre-mixing nozzle portion 21 of the inner side and an outer sleeve 23 of the outer side. While illustration is omitted, the outer sleeve 23 is supported to the pre-mixing nozzle portion 21 via a plurality of rib members. While the pre-mixing nozzle in the prior art has its front end cut at the position of its base plate without projecting further, the pre-mixing nozzle 11 of the present invention has its front end projected beyond the base plate 17 .
  • a front end of the outer sleeve 23 projects frontward beyond the position of the base plate 17 .
  • Numeral 14 designates a flame holding cone, that has its front end portion cut by the projection of the outer sleeve 23 to be made shorter.
  • Numeral 22 designates a swirler vane, construction of which is the same as that of the prior art one.
  • main fuel 40 flows into the eight pre-mixing nozzles 11 and is pre-mixed with air to form a pre-mixture for combustion in the combustion zone of the combustor 13 .
  • the air is supplied from a compressor (not shown) to be fed into the combustor 13 flowing through an inner peripheral space portion of the combustor body 10 , as shown by arrows 50 in FIG. 1( a ), and further flowing through the pre-mixing nozzle portion 21 as well as through an outer peripheral space portion of the pre-mixing nozzle portion 21 , as shown by arrows 51 in FIG. 2.
  • pilot fuel 41 is supplied into the combustor 13 through the pilot nozzle 12 of the-combustor central position and burns there together with the pre-mixture.
  • a high temperature gas inner circulating flow 15 is generated by the pilot fuel.
  • a high temperature gas outer circulating flow 16 is generated by the pre-mixture coming from the pre-mixing nozzle 11 .
  • a gas stagnation area is formed in the inner peripheral space portion of the outer cylindrical member 13 b in front of the pre-mixing nozzle 11 by the construction of the combustor 13 comprising the inner cylindrical member 13 a and the outer cylindrical member 13 b and having the inner diameter of the outer cylindrical member 13 b made larger.
  • the high temperature gas outer circulating flow 16 is formed in this gas stagnation area as a circulating flow of a high temperature combustion gas generated by combustion of the main pre-mixture.
  • the flame holding ability is greatly enhanced by the construction of the high temperature gas inner and outer circulating flows 15 , 16 .
  • the pilot fuel quantity as so far necessitated for the flame holding, can be reduced and thereby the NOx quantity generated of the pilot fuel can be reduced and a very low NOx combustion can be realized.
  • the pre-mixing nozzle 11 comprises the swirler vane 22 , the pre-mixing nozzle portion 21 and the outer sleeve 23 .
  • the outer sleeve 23 is arranged with a predetermined gap being maintained from the pre-mixing nozzle portion 21 of the inner side thereof and the air, as shown by the arrows 51 , flows into the gap, so that the pre-mixing nozzle portion 21 and the outer sleeve 23 that are heated by the high temperature gas can be sufficiently cooled.
  • the front end of the pre-mixing nozzle 11 projects beyond the base plate 17 .
  • the base plate 17 that is directly exposed to the high temperature gas outer circulating flow 16 , is prevented from being overheated.
  • L is a projecting distance of the projecting portion, that is, a distance between a front side surface of the base plate 17 and the front end of the pre-mixing nozzle 11
  • D is an outer diameter of the pre-mixing nozzle 11 , that is, an outer diameter of the outer sleeve 23
  • L is set to D/3 or more (L ⁇ D/3)
  • FIG. 3 is the same view as FIG. 1( b ) in which a hatched portion is added.
  • letter P is defined as a pitch circle that is a circle on which central axes of all of the pre-mixing nozzles 11 are arranged.
  • An inner diameter of the outer cylindrical member 13 b that corresponds to a diameter of the combustion zone in the combustor, is set such that, where an area is taken on a radial directional plane of the combustor, the area inside of the outer cylindrical member 13 b and outside of the pitch circle P, less the area taken by the pre-mixing nozzles 11 outside of the pitch circle P, that is, the area shown by the hatched portion in FIG.
  • NOx quantity of 25 PPM in the prior art can be reduced to 10 PPM or less.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
US10/198,368 2001-08-24 2002-07-19 Gas turbine combustor Abandoned US20030037549A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2001-254360 2001-08-24
JP2001254360A JP2003065537A (ja) 2001-08-24 2001-08-24 ガスタービン燃焼器

Publications (1)

Publication Number Publication Date
US20030037549A1 true US20030037549A1 (en) 2003-02-27

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ID=19082534

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/198,368 Abandoned US20030037549A1 (en) 2001-08-24 2002-07-19 Gas turbine combustor

Country Status (5)

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US (1) US20030037549A1 (fr)
EP (1) EP1288576A3 (fr)
JP (1) JP2003065537A (fr)
CN (1) CN1172116C (fr)
CA (1) CA2394118A1 (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040020210A1 (en) * 2001-06-29 2004-02-05 Katsunori Tanaka Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine
US20080078179A1 (en) * 2004-11-09 2008-04-03 Siemens Westinghouse Power Corporation Extended flashback annulus in a gas turbine combustor
US20080131824A1 (en) * 2006-10-26 2008-06-05 Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. Burner device and method for injecting a mixture of fuel and oxidant into a combustion space
US20090056336A1 (en) * 2007-08-28 2009-03-05 General Electric Company Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine
US20140109587A1 (en) * 2012-08-21 2014-04-24 General Electric Company System and method for reducing modal coupling of combustion dynamics
US20140338338A1 (en) * 2013-03-12 2014-11-20 General Electric Company System and method for tube level air flow conditioning
US9255711B2 (en) * 2012-08-21 2016-02-09 General Electric Company System for reducing combustion dynamics by varying fuel flow axial distances
CN105423342A (zh) * 2016-01-12 2016-03-23 西北工业大学 微型发动机燃烧室凹腔壁面蒸发管
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9618333B2 (en) 2012-09-24 2017-04-11 Mitsubishi Hitachi Power Systems, Ltd. Clearance measurement device and clearance measurement method for combustor
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9650959B2 (en) 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US11486301B2 (en) * 2019-01-25 2022-11-01 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor, and gas turbine

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US7007477B2 (en) * 2004-06-03 2006-03-07 General Electric Company Premixing burner with impingement cooled centerbody and method of cooling centerbody
US7540152B2 (en) * 2006-02-27 2009-06-02 Mitsubishi Heavy Industries, Ltd. Combustor
US20100192582A1 (en) * 2009-02-04 2010-08-05 Robert Bland Combustor nozzle
US8613187B2 (en) * 2009-10-23 2013-12-24 General Electric Company Fuel flexible combustor systems and methods
US8733108B2 (en) * 2010-07-09 2014-05-27 General Electric Company Combustor and combustor screech mitigation methods
US8991187B2 (en) * 2010-10-11 2015-03-31 General Electric Company Combustor with a lean pre-nozzle fuel injection system
WO2012133774A1 (fr) * 2011-03-30 2012-10-04 三菱重工業株式会社 Buse, chambre de combustion de turbine à gaz et turbine à gaz
CN102425793A (zh) * 2011-10-19 2012-04-25 中国科学院广州能源研究所 自回热型低热值燃气旋流燃烧装置
JP6002313B2 (ja) * 2012-03-29 2016-10-05 エクソンモービル アップストリーム リサーチ カンパニー ターボ機械用燃焼器組立体
EP2700879B1 (fr) * 2012-08-24 2019-03-27 Ansaldo Energia Switzerland AG Procédé pour mélanger un air de dilution dans un système de combustion séquentielle d'une turbine à gaz, et système de combustion séquentielle pour une turbine à gaz comprenant un injecteur d'air de dilution
JP6037736B2 (ja) * 2012-09-11 2016-12-07 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器およびこれを備えたガスタービン機関
JP6331662B2 (ja) * 2014-05-07 2018-05-30 三浦工業株式会社 ガスバーナ
US10415831B2 (en) * 2016-10-27 2019-09-17 General Electric Company Combustor assembly with mounted auxiliary component
CN109340750B (zh) * 2017-11-06 2019-11-12 北京东元同创能源技术有限公司 一种低氮氧化物排放的方法及实现该方法的燃气燃烧器
CN107726317A (zh) * 2017-11-29 2018-02-23 上海钜荷热力技术有限公司 一种带冷却装置的平板燃烧器
CN109654538B (zh) * 2018-12-07 2021-02-12 中国航发沈阳发动机研究所 一种利于降低火焰筒壁温的文丘里管
CN109611891B (zh) * 2018-12-16 2020-11-06 中国航发沈阳发动机研究所 一种干低排放燃烧器
CN113739204B (zh) * 2021-08-23 2023-02-03 四川航天中天动力装备有限责任公司 一种回流燃烧室用带气动的离心回流式燃油喷嘴
CN115325569B (zh) * 2022-09-02 2023-05-26 华能国际电力股份有限公司 一种燃烧室、燃气轮机及燃烧控制方法

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US6082111A (en) * 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors

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DE69910106T2 (de) * 1998-04-15 2004-06-17 Mitsubishi Heavy Industries, Ltd. Brennkammer
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US5259184A (en) * 1992-03-30 1993-11-09 General Electric Company Dry low NOx single stage dual mode combustor construction for a gas turbine
US5274991A (en) * 1992-03-30 1994-01-04 General Electric Company Dry low NOx multi-nozzle combustion liner cap assembly
US5836164A (en) * 1995-01-30 1998-11-17 Hitachi, Ltd. Gas turbine combustor
US6082111A (en) * 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7171813B2 (en) * 2001-06-29 2007-02-06 Mitsubishi Heavy Metal Industries, Ltd. Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine
US20040020210A1 (en) * 2001-06-29 2004-02-05 Katsunori Tanaka Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine
US20080078179A1 (en) * 2004-11-09 2008-04-03 Siemens Westinghouse Power Corporation Extended flashback annulus in a gas turbine combustor
US7370466B2 (en) * 2004-11-09 2008-05-13 Siemens Power Generation, Inc. Extended flashback annulus in a gas turbine combustor
US20080131824A1 (en) * 2006-10-26 2008-06-05 Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. Burner device and method for injecting a mixture of fuel and oxidant into a combustion space
US20090056336A1 (en) * 2007-08-28 2009-03-05 General Electric Company Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine
US20140109587A1 (en) * 2012-08-21 2014-04-24 General Electric Company System and method for reducing modal coupling of combustion dynamics
US9151502B2 (en) * 2012-08-21 2015-10-06 General Electric Company System and method for reducing modal coupling of combustion dynamics
US9255711B2 (en) * 2012-08-21 2016-02-09 General Electric Company System for reducing combustion dynamics by varying fuel flow axial distances
US9618333B2 (en) 2012-09-24 2017-04-11 Mitsubishi Hitachi Power Systems, Ltd. Clearance measurement device and clearance measurement method for combustor
US9650959B2 (en) 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US20140338338A1 (en) * 2013-03-12 2014-11-20 General Electric Company System and method for tube level air flow conditioning
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US9765973B2 (en) * 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
CN105423342A (zh) * 2016-01-12 2016-03-23 西北工业大学 微型发动机燃烧室凹腔壁面蒸发管
US11486301B2 (en) * 2019-01-25 2022-11-01 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor, and gas turbine

Also Published As

Publication number Publication date
CN1403745A (zh) 2003-03-19
CA2394118A1 (fr) 2003-02-24
EP1288576A2 (fr) 2003-03-05
JP2003065537A (ja) 2003-03-05
EP1288576A3 (fr) 2004-01-07
CN1172116C (zh) 2004-10-20

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