CN101737801A - 燃气轮机中的一体化的燃烧器和一级喷嘴以及方法 - Google Patents

燃气轮机中的一体化的燃烧器和一级喷嘴以及方法 Download PDF

Info

Publication number
CN101737801A
CN101737801A CN200910226044A CN200910226044A CN101737801A CN 101737801 A CN101737801 A CN 101737801A CN 200910226044 A CN200910226044 A CN 200910226044A CN 200910226044 A CN200910226044 A CN 200910226044A CN 101737801 A CN101737801 A CN 101737801A
Authority
CN
China
Prior art keywords
fuel
jet nozzle
order jet
incorporate
transition piece
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.)
Granted
Application number
CN200910226044A
Other languages
English (en)
Other versions
CN101737801B (zh
Inventor
L·B·小戴维斯
W·S·齐明斯基
K·W·麦马汉
R·J·基拉
S·A·梅什科夫
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.)
General Electric Co PLC
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of CN101737801A publication Critical patent/CN101737801A/zh
Application granted granted Critical
Publication of CN101737801B publication Critical patent/CN101737801B/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/42—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
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

本发明涉及燃气轮机中的一体化的燃烧器和一级喷嘴以及方法。一种燃气轮机中的一体化的燃烧器和一级喷嘴包括燃烧室(22)，该燃烧室(22)从分开的轴向位置处的至少一个燃料喷嘴组(24)接收预混合的燃料和空气。燃烧室包括将热的燃烧气体传送给涡轮的衬套(26)和过渡件(28)。一级喷嘴、衬套和过渡件被一体化成单个部件。一个或多个燃料喷嘴组的轴向位置中的至少一个包括使放热集中并减小火焰长度的多个小型混合装置(30)。

Description

燃气轮机中的一体化的燃烧器和一级喷嘴以及方法
技术领域
本发明涉及燃气轮机的燃烧器，且更具体地说，涉及一种用于燃气轮机的一体化的燃烧器和一级喷嘴。
背景技术
燃气轮机发动机通常包括压缩机段、燃烧器段和至少一个涡轮段。压缩机压缩空气，该空气与燃料相混合，并被引导至燃烧器中。然后点燃混合物以产生热的燃烧气体。燃烧气体被引导至涡轮中，涡轮从该燃烧气体中吸取能量，以用于为压缩机提供动力，以及用于产生有用功来为负载-例如发电机-提供动力。
通常，燃烧段与下游涡轮是不同的且分开的。具体地说，对于罐式-环形设计，这两个构件-燃烧器和涡轮-在燃烧过渡件和涡轮第一级喷嘴的交接处相遇。这个交接处需要使用密封件，以便最大限度地减小进入气道中的泄漏。这些泄漏影响燃烧器的排放能力(即NOx)，因为对于相同的涡轮入口温度，大的泄漏将导致升高的燃烧温度。因而希望消除密封件，并通过将第一级喷嘴集成到过渡件设计中来减少部件数量。
过渡件长度-以及整个燃烧器长度-受到完全燃烧所需要的时间驱动(尤其在部分功率环境下)。该长度传统上太长，以至于实际上不能将过渡件与一级喷嘴组合起来(从制造方面和适应涡轮/燃烧器交接处的相对运动的观点两者来看)。因此，为了将第一级喷嘴集成到过渡件设计中，希望减小燃烧器的长度。
发明内容
在一个示例性实施例中，燃气轮机中的一体化的燃烧器和一级喷嘴包括燃烧室，其从分开的轴向位置处的至少一个燃料喷嘴组接收预混合的燃料和空气。该燃烧室包括将热的燃烧气体传送给涡轮的衬套和过渡件。一级喷嘴、衬套和过渡件被一体化成单个部件。一个或多个燃料喷嘴组的轴向位置中的至少一个包括使放热集中并减小火焰长度的多个小型混合装置。
在另一示例性实施例中，一体化的燃烧器和一级喷嘴包括从分开的轴向位置处的至少一个燃料喷嘴组接收预混合的燃料和空气的燃烧室。该燃烧室包括将热的燃烧气体传送给涡轮的衬套和过渡件。一个或多个燃料喷嘴组的轴向位置中的至少一个包括使放热集中并减小火焰长度的多个小型混合装置。减小的火焰长度使得一级喷嘴、衬套和过渡件能够一体化成单个部件。
在又一示例性实施例中，一种使燃气轮机中的燃烧器和一级喷嘴一体化的方法包括如下步骤：将燃烧室布置成以便从分开的轴向位置处的至少一个燃料喷嘴组接收预混合的燃料和空气，其中，该燃烧室包括将热的燃烧气体传送给涡轮的衬套和过渡件；为一个或多个燃料喷嘴组的轴向位置中的至少一个提供使放热集中并减小火焰长度的多个小型混合装置；以及通过减小的火焰长度而将一级喷嘴、衬套和过渡件一体化成单个部件。
附图说明
图1是传统的″长的″燃烧器的截面图；
图2是所述实施例的″紧凑型″的一体化的燃烧器的截面图；
图3是将预混合的燃料和空气传送到燃烧器中的小型混合器快速混合喷嘴的近视图；
图4和图5显示了一体化的燃烧器和一级喷嘴与一级涡轮叶片之间的交接处的备选实施例；和
图6是一体化的燃烧器和一级喷嘴的透视图。
部件列表：
10燃烧器；
12衬套；
14过渡件；
20一体化的燃烧器/S1喷嘴；
22燃烧室；
24燃料喷嘴组；
26燃烧衬套；
28过渡件；
29一级喷嘴；
30小型混合装置；
32第二级燃料喷射器；
34扼流端；
36扩展护罩；
具体实施方式
图1显示了用于燃气轮机的现有技术燃烧器，燃气轮机包括压缩机、多个燃烧器和涡轮。虽然没有特别显示，但涡轮沿着公共轴线而传动地连接在压缩机上。压缩机将进气加压，之后进气逆向流向燃烧器，此处其用于冷却燃烧器，并为燃烧过程提供空气。燃烧器10包括衬套12和过渡件14，衬套12限定了燃烧区域，过渡件14将燃烧器的出口端与涡轮的入口端连接起来，以便将热的燃烧产物传送给涡轮。注意，燃烧过渡件14和涡轮第一级喷嘴之间的交接处需要使用密封件，以便最大限度地减小进入气道的泄漏。在所述的实施例中提出将一级喷嘴集成到过渡件设计中。
图2是一体化的燃烧器和一级喷嘴20的截面图。该结构包括燃烧室22，其从分开的轴向位置处的至少一个燃料喷嘴组24接收预混合的燃料和空气。燃烧室22包括经由一级喷嘴29将热的燃烧气体传送给涡轮的燃烧衬套26和过渡件28。如图2中所示，一级喷嘴29、衬套26和过渡件28被一体化成单个部件。图6是该组件的透视图。
图3是在一个或多个燃料喷嘴组24的轴向位置中的至少一个处提供的小型混合器快速混合喷嘴的近视图。小型混合装置30用于使放热集中，并减小特征火焰长度。如图所示，轴向位置包括三十一个快速混合喷嘴，但本发明并不意图局限于所示结构。同采用具有大约为衬套直径(或对于环形设计为衬套高度)1/3的长度大小的混合喷嘴的传统设计相比，混合元件30优选具有大约为衬套直径1/10至1/100的长度大小。同图1中所显示的现有技术的″长″燃烧器相比，由小型混合装置30提供的集中式放热和特征火焰长度的减小使得一级喷嘴、衬套和过渡件能够一体化成单个部件，从而形成图2中所示的″紧凑型″燃烧器。
混合元件30可如同许多现代设计那样排列在单个平面中，或多个轴向位置上。不管轴向布置如何，对于各个轴向位置，燃烧器都组织成以便具有单个燃烧器水平上的燃料控制。这种局部燃料控制水平用于最大限度地减小会降低现代设计性能的变化。在一个实施例中，第二级燃料喷射器32设置在过渡件28中。在这方面，燃料控制器包括燃料回路，其可控制地在第一级燃料喷射器和第二级燃料喷射器之间分割燃料流。以与当前主导的、装置水平上的燃料控制实践相对的方式提供单个燃烧器水平上的燃料控制。也就是说，在大多数罐式-环形燃烧器装置中，燃料将通过将所有罐连接到一个控制阀上的歧管进行控制。相反，对于罐水平上的控制，各个腔室具有其自身的控制阀。因而，燃气轮机周围的歧管管路布置或气流分布的内在不均匀性可通过调整流向各个燃烧器罐的燃料流来消除，从而使得对于所有的燃烧器罐都可获得均匀的燃料-空气比。通过局部燃料控制来驱除变化的能力消除了装配多腔室阵列可能需要的任何额外的长度。这种由小型混合装置30提供的与紧凑放热相结合的燃料控制更好地使得衬套、过渡件和一级喷嘴能够一体化成单个部件。
图4和图5显示了用于一体化的结构的备选实施例。在图4中，过渡件28包括扼流端34，其以合适的角度朝向一级涡轮叶片(S1B)引导热的燃烧气体流。在这个实施例中，过渡件的扼流端34用作一级喷嘴。在图5中，过渡件28包括围绕一级喷嘴而设置的扩展护罩36，其中扩展护罩和一级喷嘴以合适的角度朝向一级涡轮叶片S1B引导热的燃烧气体流。
本文所述的实施例通过减小燃烧器长度而使燃烧器与涡轮一体化。通过使放热集中以及减少腔室与腔室之间的变化来减小燃烧器长度。一体化的结构容许减少完成针对燃气轮机设计的加热和节流所需要的部件数量。减少的部件数量还将减少费用和停工时间。
虽然已经结合目前被认为是最实用的和优选的实施例的内容描述了本发明，但是将理解的是，本发明并不局限于所公开的实施例，相反，其意图覆盖包含在所附的权利要求的精神和范围内的各种变体和等效装置。

Claims (10)

1.一种燃气轮机中的一体化的燃烧器和一级喷嘴，包括从分开的轴向位置处的至少一个燃料喷嘴组(24)接收预混合的燃料和空气的燃烧室(22)，所述燃烧室包括将热的燃烧气体传送给涡轮的衬套(26)和过渡件(28)，其中，所述一级喷嘴(29)、所述衬套(26)和所述过渡件(28)被一体化成单个部件，一个或多个燃料喷嘴组的轴向位置中的至少一个包括使放热集中并减小火焰长度的多个小型混合装置(30)。
2.根据权利要求1所述的一体化的燃烧器和一级喷嘴，其特征在于，所述小型混合装置(30)布置在单个平面或多个轴向位置其中一种上，并包括用于各个轴向位置的燃料控制器。
3.根据权利要求2所述的一体化的燃烧器和一级喷嘴，其特征在于，还包括能够与所述至少一个燃料喷嘴组协作的至少一个第一级燃料喷射器和设置在所述过渡件(28)中的第二级燃料喷射器(32)，其中，所述燃料控制器包括可控制地在所述至少一个第一级燃料喷射器和所述第二级燃料喷射器之间分割燃料流的燃料回路。
4.根据权利要求1所述的一体化的燃烧器和一级喷嘴，其特征在于，所述混合装置(30)具有衬套直径的1/10至1/100的长度大小。
5.根据权利要求1所述的一体化的燃烧器和一级喷嘴，其特征在于，所述混合装置(30)以阵列形式布置在单个平面中。
6.根据权利要求1所述的一体化的燃烧器和一级喷嘴，其特征在于，所述混合装置(30)以阵列形式布置在多个轴向位置上。
7.根据权利要求1所述的一体化的燃烧器和一级喷嘴，其特征在于，所述燃气轮机包括与所述单个部件相邻地设置的一级涡轮叶片，并且，其中，所述过渡件包括以合适的角度朝向所述一级涡轮叶片引导所述热的燃烧气体流的扼流端(34)。
8.根据权利要求7所述的一体化的燃烧器和一级喷嘴，其特征在于，所述过渡件的扼流端(34)用作所述一级喷嘴。
9.根据权利要求1所述的一体化的燃烧器和一级喷嘴，其特征在于，所述燃气轮机包括与所述单个部件相邻地设置的一级涡轮叶片，并且，其中，所述过渡件包括围绕所述一级喷嘴而设置的扩展护罩(36)，所述扩展护罩和所述一级喷嘴以合适的角度朝向所述一级涡轮叶片引导所述热的燃烧气体流。
10.一种使燃气轮机中的燃烧器和一级喷嘴一体化的方法，所述方法包括：
将燃烧室(22)布置成以便从分开的轴向位置处的至少一个燃料喷嘴组(24)接收预混合的燃料和空气，其中，所述燃烧室包括将热的燃烧气体传送给涡轮的衬套(26)和过渡件(28)；
为一个或多个燃料喷嘴组的轴向位置中的至少一个提供使放热集中并减小火焰长度的多个小型混合装置(30)；以及
通过所述减小的火焰长度而将所述一级喷嘴、所述衬套和所述过渡件一体化成单个部件。
CN200910226044.5A 2008-11-12 2009-11-12 燃气轮机中的一体化的燃烧器和一级喷嘴以及方法 Active CN101737801B (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/269,411 2008-11-12
US12/269,411 US9822649B2 (en) 2008-11-12 2008-11-12 Integrated combustor and stage 1 nozzle in a gas turbine and method

Publications (2)

Publication Number Publication Date
CN101737801A true CN101737801A (zh) 2010-06-16
CN101737801B CN101737801B (zh) 2014-12-10

Family

ID=42105342

Family Applications (1)

Application Number Title Priority Date Filing Date
CN200910226044.5A Active CN101737801B (zh) 2008-11-12 2009-11-12 燃气轮机中的一体化的燃烧器和一级喷嘴以及方法

Country Status (4)

Country Link
US (1) US9822649B2 (zh)
JP (1) JP5544141B2 (zh)
CN (1) CN101737801B (zh)
DE (1) DE102009044513B4 (zh)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102840600A (zh) * 2011-06-21 2012-12-26 通用电气公司 用于从过渡喷嘴传递热量的方法和系统
CN102853451A (zh) * 2011-06-21 2013-01-02 通用电气公司 用于冷却过渡喷嘴的方法和系统
CN102865145A (zh) * 2011-07-05 2013-01-09 通用电气公司 用于涡轮机系统中的过渡管道的支承组件
CN103062795A (zh) * 2011-10-18 2013-04-24 通用电气公司 过渡喷嘴
CN103471134A (zh) * 2012-06-05 2013-12-25 通用电气公司 冲击冷却的燃烧器
CN103850796A (zh) * 2012-11-30 2014-06-11 通用电气公司 燃气涡轮发动机系统及其相关方法
CN103975130A (zh) * 2011-10-04 2014-08-06 西门子能量股份有限公司 用于燃气轮机的壳体
CN104220702A (zh) * 2012-04-11 2014-12-17 斯奈克玛 涡轮发动机，例如涡轮喷气发动机或涡轮螺旋桨发动机
CN104619956A (zh) * 2012-09-04 2015-05-13 西门子能量股份有限公司 具有径向扩散器和缩短中段的燃气涡轮发动机
CN110234845A (zh) * 2017-01-27 2019-09-13 通用电气公司 一体流动路径结构

Families Citing this family (49)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5180807B2 (ja) 2008-12-24 2013-04-10 三菱重工業株式会社 １段静翼の冷却構造、及びガスタービン
US8112216B2 (en) * 2009-01-07 2012-02-07 General Electric Company Late lean injection with adjustable air splits
US8701418B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection for fuel flexibility
US8707707B2 (en) * 2009-01-07 2014-04-29 General Electric Company Late lean injection fuel staging configurations
US8701383B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection system configuration
US8701382B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection with expanded fuel flexibility
US8683808B2 (en) * 2009-01-07 2014-04-01 General Electric Company Late lean injection control strategy
JP5479058B2 (ja) * 2009-12-07 2014-04-23 三菱重工業株式会社 燃焼器とタービン部との連通構造、および、ガスタービン
US8978388B2 (en) 2011-06-03 2015-03-17 General Electric Company Load member for transition duct in turbine system
US20120324898A1 (en) * 2011-06-21 2012-12-27 Mcmahan Kevin Weston Combustor assembly for use in a turbine engine and methods of assembling same
US8650852B2 (en) * 2011-07-05 2014-02-18 General Electric Company Support assembly for transition duct in turbine system
JP5848074B2 (ja) * 2011-09-16 2016-01-27 三菱日立パワーシステムズ株式会社 ガスタービン、尾筒及び燃焼器
US9328623B2 (en) * 2011-10-05 2016-05-03 General Electric Company Turbine system
US8974179B2 (en) 2011-11-09 2015-03-10 General Electric Company Convolution seal for transition duct in turbine system
US8701415B2 (en) 2011-11-09 2014-04-22 General Electric Company Flexible metallic seal for transition duct in turbine system
US8459041B2 (en) 2011-11-09 2013-06-11 General Electric Company Leaf seal for transition duct in turbine system
US9145778B2 (en) * 2012-04-03 2015-09-29 General Electric Company Combustor with non-circular head end
US9506359B2 (en) * 2012-04-03 2016-11-29 General Electric Company Transition nozzle combustion system
US20130283802A1 (en) * 2012-04-27 2013-10-31 General Electric Company Combustor
US9133722B2 (en) * 2012-04-30 2015-09-15 General Electric Company Transition duct with late injection in turbine system
US9038394B2 (en) 2012-04-30 2015-05-26 General Electric Company Convolution seal for transition duct in turbine system
EP2725196A1 (en) * 2012-10-24 2014-04-30 Alstom Technology Ltd Combustor transition
EP2725197A1 (en) 2012-10-24 2014-04-30 Alstom Technology Ltd Combustor transition
US20140127008A1 (en) * 2012-11-08 2014-05-08 General Electric Company Transition duct having airfoil and hot gas path assembly for turbomachine
US8707673B1 (en) * 2013-01-04 2014-04-29 General Electric Company Articulated transition duct in turbomachine
US9482434B2 (en) 2013-03-15 2016-11-01 General Electric Company Methods relating to downstream fuel and air injection in gas turbines
US9435541B2 (en) 2013-03-15 2016-09-06 General Electric Company Systems and apparatus relating to downstream fuel and air injection in gas turbines
US9714768B2 (en) 2013-03-15 2017-07-25 General Electric Company Systems and apparatus relating to downstream fuel and air injection in gas turbines
US9528439B2 (en) 2013-03-15 2016-12-27 General Electric Company Systems and apparatus relating to downstream fuel and air injection in gas turbines
US9080447B2 (en) 2013-03-21 2015-07-14 General Electric Company Transition duct with divided upstream and downstream portions
US9458732B2 (en) 2013-10-25 2016-10-04 General Electric Company Transition duct assembly with modified trailing edge in turbine system
US9528706B2 (en) * 2013-12-13 2016-12-27 Siemens Energy, Inc. Swirling midframe flow for gas turbine engine having advanced transitions
US9593853B2 (en) 2014-02-20 2017-03-14 Siemens Energy, Inc. Gas flow path for a gas turbine engine
US20150323185A1 (en) 2014-05-07 2015-11-12 General Electric Compamy Turbine engine and method of assembling thereof
US10024180B2 (en) * 2014-11-20 2018-07-17 Siemens Energy, Inc. Transition duct arrangement in a gas turbine engine
US10072846B2 (en) * 2015-07-06 2018-09-11 General Electric Company Trapped vortex cavity staging in a combustor
EP3124749B1 (en) * 2015-07-28 2018-12-19 Ansaldo Energia Switzerland AG First stage turbine vane arrangement
US10260752B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US10227883B2 (en) 2016-03-24 2019-03-12 General Electric Company Transition duct assembly
US10260360B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly
US10260424B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US10145251B2 (en) 2016-03-24 2018-12-04 General Electric Company Transition duct assembly
US10823418B2 (en) 2017-03-02 2020-11-03 General Electric Company Gas turbine engine combustor comprising air inlet tubes arranged around the combustor
US10837299B2 (en) 2017-03-07 2020-11-17 General Electric Company System and method for transition piece seal
JP6871377B2 (ja) * 2017-06-29 2021-05-12 三菱パワー株式会社 ガスタービンの１段静翼、ガスタービン、ガスタービンの静翼ユニット及び燃焼器アセンブリ
US11181005B2 (en) 2018-05-18 2021-11-23 Raytheon Technologies Corporation Gas turbine engine assembly with mid-vane outer platform gap
US11480337B2 (en) 2019-11-26 2022-10-25 Collins Engine Nozzles, Inc. Fuel injection for integral combustor and turbine vane
CN114838386B (zh) * 2022-04-20 2023-06-23 中国航发沈阳发动机研究所 一种用于低污染燃烧室的气体燃料喷嘴
CN116202104B (zh) * 2023-02-06 2024-05-07 中国科学院工程热物理研究所 一种燃气轮机多喷嘴阵列增稳燃烧室

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1188210A (zh) * 1996-12-13 1998-07-22 亚瑞亚·勃朗勃威力有限公司 具有组合在一起的导向叶片的燃烧室
CN1401938A (zh) * 2001-08-29 2003-03-12 株式会社日立制作所 燃气轮机燃烧器及其操作方法
US20040088990A1 (en) * 2002-11-07 2004-05-13 Siemens Westinghouse Power Corporation Integrated combustor and nozzle for a gas turbine combustion system
CN1549886A (zh) * 2001-09-03 2004-11-24 西门子公司 燃气轮机的燃烧室中间段
EP1903184A2 (en) * 2006-09-21 2008-03-26 Siemens Power Generation, Inc. Combustion transition duct providing stage 1 tangential turning for turbine engines
CN101285591A (zh) * 2008-04-22 2008-10-15 北京航空航天大学 一种一体化燃油喷射径向旋流器预混预蒸发低污染燃烧室
EP1985927A2 (en) * 2007-04-27 2008-10-29 General Electric Company Methods and systems to facilitate reducing NOx emissions in combustion systems

Family Cites Families (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3018624A (en) * 1954-03-02 1962-01-30 Bristol Siddeley Engines Ltd Flame tubes for use in combustion systems of gas turbine engines
US4023919A (en) * 1974-12-19 1977-05-17 General Electric Company Thermal actuated valve for clearance control
US4409787A (en) * 1979-04-30 1983-10-18 General Electric Company Acoustically tuned combustor
US4445339A (en) * 1980-11-24 1984-05-01 General Electric Co. Wingtip vortex flame stabilizer for gas turbine combustor flame holder
US4432207A (en) * 1981-08-06 1984-02-21 General Electric Company Modular catalytic combustion bed support system
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
US4928481A (en) * 1988-07-13 1990-05-29 Prutech Ii Staged low NOx premix gas turbine combustor
US5000004A (en) * 1988-08-16 1991-03-19 Kabushiki Kaisha Toshiba Gas turbine combustor
US5749219A (en) * 1989-11-30 1998-05-12 United Technologies Corporation Combustor with first and second zones
US5203796A (en) * 1990-08-28 1993-04-20 General Electric Company Two stage v-gutter fuel injection mixer
US5289677A (en) * 1992-12-16 1994-03-01 United Technologies Corporation Combined support and seal ring for a combustor
US5491970A (en) * 1994-06-10 1996-02-20 General Electric Co. Method for staging fuel in a turbine between diffusion and premixed operations
US5749701A (en) * 1996-10-28 1998-05-12 General Electric Company Interstage seal assembly for a turbine
US6089025A (en) * 1998-08-24 2000-07-18 General Electric Company Combustor baffle
US6250063B1 (en) * 1999-08-19 2001-06-26 General Electric Co. Fuel staging apparatus and methods for gas turbine nozzles
FI112681B (fi) * 1999-08-24 2003-12-31 Metso Paper Inc Menetelmä ja sovitelma paperi- ja/tai kartonkirainan pintakäsittelyä varten
US6220815B1 (en) * 1999-12-17 2001-04-24 General Electric Company Inter-stage seal retainer and assembly
US6415608B1 (en) * 2000-09-26 2002-07-09 Siemens Westinghouse Power Corporation Piloted rich-catalytic lean-burn hybrid combustor
US6633623B2 (en) * 2000-11-29 2003-10-14 General Electric Company Apparatus and methods for protecting a jet pump nozzle assembly and inlet-mixer
US6928823B2 (en) * 2001-08-29 2005-08-16 Hitachi, Ltd. Gas turbine combustor and operating method thereof
US6680549B2 (en) * 2001-11-01 2004-01-20 General Electric Company Tapered rotor-stator air gap for superconducting synchronous machine
US6840048B2 (en) * 2002-09-26 2005-01-11 General Electric Company Dynamically uncoupled can combustor
US6882068B2 (en) * 2002-10-08 2005-04-19 General Electric Company Forced air stator ventilation system and stator ventilation method for superconducting synchronous machine
US7185494B2 (en) * 2004-04-12 2007-03-06 General Electric Company Reduced center burner in multi-burner combustor and method for operating the combustor
US7337057B2 (en) * 2004-05-28 2008-02-26 General Electric Company Methods and apparatus for predicting and/or for avoiding lean blow-outs
US6979118B1 (en) 2004-06-01 2005-12-27 General Electric Company Estimating combustor flame temperature based on frequency of combustor dynamics transverse mode
US6993916B2 (en) * 2004-06-08 2006-02-07 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
US7278266B2 (en) * 2004-08-31 2007-10-09 General Electric Company Methods and apparatus for gas turbine engine lean blowout avoidance
US7210297B2 (en) * 2004-11-04 2007-05-01 General Electric Company Method and apparatus for identification of hot and cold chambers in a gas turbine combustor
US7082766B1 (en) * 2005-03-02 2006-08-01 General Electric Company One-piece can combustor
US7441398B2 (en) * 2005-05-20 2008-10-28 General Electric Company NOx adjustment system for gas turbine combustors
US7490471B2 (en) * 2005-12-08 2009-02-17 General Electric Company Swirler assembly
GB2445565A (en) 2006-09-26 2008-07-16 Siemens Ag Gas turbine engine having a plurality of modules comprising a combustor and transition duct
JP5023687B2 (ja) 2006-12-20 2012-09-12 株式会社Ｉｈｉ 燃焼器及びガスタービン
US7665309B2 (en) * 2007-09-14 2010-02-23 Siemens Energy, Inc. Secondary fuel delivery system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1188210A (zh) * 1996-12-13 1998-07-22 亚瑞亚·勃朗勃威力有限公司 具有组合在一起的导向叶片的燃烧室
CN1401938A (zh) * 2001-08-29 2003-03-12 株式会社日立制作所 燃气轮机燃烧器及其操作方法
CN1549886A (zh) * 2001-09-03 2004-11-24 西门子公司 燃气轮机的燃烧室中间段
US20040088990A1 (en) * 2002-11-07 2004-05-13 Siemens Westinghouse Power Corporation Integrated combustor and nozzle for a gas turbine combustion system
EP1903184A2 (en) * 2006-09-21 2008-03-26 Siemens Power Generation, Inc. Combustion transition duct providing stage 1 tangential turning for turbine engines
EP1985927A2 (en) * 2007-04-27 2008-10-29 General Electric Company Methods and systems to facilitate reducing NOx emissions in combustion systems
CN101285591A (zh) * 2008-04-22 2008-10-15 北京航空航天大学 一种一体化燃油喷射径向旋流器预混预蒸发低污染燃烧室

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102853451A (zh) * 2011-06-21 2013-01-02 通用电气公司 用于冷却过渡喷嘴的方法和系统
CN102840600A (zh) * 2011-06-21 2012-12-26 通用电气公司 用于从过渡喷嘴传递热量的方法和系统
CN102840600B (zh) * 2011-06-21 2017-04-12 通用电气公司 涡轮组件以及用于与其一起使用的过渡喷嘴
CN102853451B (zh) * 2011-06-21 2016-12-21 通用电气公司 用于冷却过渡喷嘴的方法和系统
CN102865145A (zh) * 2011-07-05 2013-01-09 通用电气公司 用于涡轮机系统中的过渡管道的支承组件
CN103975130A (zh) * 2011-10-04 2014-08-06 西门子能量股份有限公司 用于燃气轮机的壳体
CN103975130B (zh) * 2011-10-04 2017-03-01 西门子能量股份有限公司 用于环罐式燃气轮机的壳体
US9388738B2 (en) 2011-10-04 2016-07-12 Siemens Energy, Inc. Casing for a gas turbine engine
CN103062795B (zh) * 2011-10-18 2017-03-01 通用电气公司 过渡喷嘴
CN103062795A (zh) * 2011-10-18 2013-04-24 通用电气公司 过渡喷嘴
CN104220702A (zh) * 2012-04-11 2014-12-17 斯奈克玛 涡轮发动机，例如涡轮喷气发动机或涡轮螺旋桨发动机
CN103471134A (zh) * 2012-06-05 2013-12-25 通用电气公司 冲击冷却的燃烧器
CN104619956A (zh) * 2012-09-04 2015-05-13 西门子能量股份有限公司 具有径向扩散器和缩短中段的燃气涡轮发动机
CN104619956B (zh) * 2012-09-04 2017-06-09 西门子能量股份有限公司 具有径向扩散器和缩短中段的燃气涡轮发动机
CN103850796A (zh) * 2012-11-30 2014-06-11 通用电气公司 燃气涡轮发动机系统及其相关方法
CN110234845A (zh) * 2017-01-27 2019-09-13 通用电气公司 一体流动路径结构
CN110234845B (zh) * 2017-01-27 2022-01-11 通用电气公司 一体流动路径结构

Also Published As

Publication number Publication date
DE102009044513A1 (de) 2010-05-20
US20100115953A1 (en) 2010-05-13
CN101737801B (zh) 2014-12-10
JP5544141B2 (ja) 2014-07-09
US9822649B2 (en) 2017-11-21
JP2010117124A (ja) 2010-05-27
DE102009044513B4 (de) 2021-02-04

Similar Documents

Publication Publication Date Title
CN101737801B (zh) 燃气轮机中的一体化的燃烧器和一级喷嘴以及方法
EP2554905B1 (en) Assemblies and apparatus related to integrating late lean injection into combustion turbine engines
EP2554910B1 (en) Methods relating to integrating late lean injection into combustion turbine engines
EP2375167B1 (en) Combustor exit temperature profile control via fuel staging and related method
CN102135034B (zh) 用于燃气轮机的放出式扩散器供送型次级燃烧系统
US9010120B2 (en) Assemblies and apparatus related to integrating late lean injection into combustion turbine engines
US8863523B2 (en) System for supplying a working fluid to a combustor
EP3220047B1 (en) Gas turbine flow sleeve mounting
US20100170253A1 (en) Method and apparatus for fuel injection in a turbine engine
US9133767B2 (en) Fuel injecting assembly for gas turbine engine including cooling gap between supply structures
US20100162710A1 (en) Pre-Mix Combustion System for a Gas Turbine and Method of Operating of operating the same
CN101373075A (zh) 涡轮机燃料输送设备和系统
US8745986B2 (en) System and method of supplying fuel to a gas turbine
CN102192509A (zh) 用于改变燃烧器中空气流量的系统和方法
EP2515042A2 (en) Aerodynamic fuel nozzle
EP2664854B1 (en) Secondary combustion system
CA3149083A1 (en) Dual pressure fuel nozzles
US20150059352A1 (en) Dual fuel combustor for a gas turbine engine
CN102620316A (zh) 用于在涡轮发动机中使用的燃料喷射组件及其组装方法
US20100192587A1 (en) Combustor assembly for use in a gas turbine engine and method of assembling same
CN113864818A (zh) 燃烧器空气流动路径
US20180340689A1 (en) Low Profile Axially Staged Fuel Injector
CN102235245A (zh) 用于燃气涡轮机的流体冷却的注射喷嘴组件
US20180231255A1 (en) Burner assembly for a combustor of a gas turbine power plant and combustor comprising said burner assembly
US11692711B2 (en) Pilot burner for combustor

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant
TR01 Transfer of patent right
TR01 Transfer of patent right

Effective date of registration: 20240104

Address after: Swiss Baden

Patentee after: GENERAL ELECTRIC CO. LTD.

Address before: New York, United States

Patentee before: General Electric Co.