CN101799162A - 用于涡轮机的束状多管式喷嘴 - Google Patents

用于涡轮机的束状多管式喷嘴 Download PDF

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CN101799162A
CN101799162A CN200910224888A CN200910224888A CN101799162A CN 101799162 A CN101799162 A CN 101799162A CN 200910224888 A CN200910224888 A CN 200910224888A CN 200910224888 A CN200910224888 A CN 200910224888A CN 101799162 A CN101799162 A CN 101799162A
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tube assemblies
bundled
bundled mini
turbine
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CN101799162B (zh
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B·P·莱西
W·S·兹明斯基
T·E·约翰逊
左柏芳
W·D·约克
J·H·吴
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General Electric Co PLC
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    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • 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
    • 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
    • F23D2900/00012—Liquid or gas fuel burners with flames spread over a flat surface, either premix or non-premix type, e.g. "Flächenbrenner"

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  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

本发明涉及一种用于涡轮机的束状多管式喷嘴，该涡轮机包括压缩机、可操作地连接到压缩机的燃烧器、安装到燃烧器上的端盖和可操作地连接到燃烧器的喷嘴组件。喷嘴组件包括具有延伸到第二表面的第一表面的帽状部件。帽状部件还包括多个开口。多个束状微管组件可拆卸地安装在帽状部件的多个开口中。多个束状微管组件各包括具有第一端部和第二端部的主体部。流体室布置在主体部内。多个管在第一端部和第二端部之间延伸。多个管各流体式连接到流体室。

Description

用于涡轮机的束状多管式喷嘴
技术领域
本申请公开的主题涉及涡轮机领域，更具体地涉及用于涡轮机的束状多管式喷嘴。
背景技术
通常，燃气涡轮发动机燃烧释放热能的燃料/空气混合物以形成高温气流。该高温气流经由热气通道引导到涡轮。涡轮将来自高温气流的热能转换成使涡轮轴旋转的机械能。涡轮可用于多种应用，诸如用于为泵或发电机提供动力。
在燃气涡轮中，发动机效率随着燃烧气流温度增加而增加。不幸的是，更高的气流温度产生更高的氮氧化物(NOx)水平，该氮氧化物是受联邦和州法规限制的排放物。因此，在高效的范围内操作燃气涡轮与同时确保NOx的排出量仍然低于要求水平之间存在细致的平衡作用。一种实现低NOx水平的方法是确保在燃烧前燃料和空气的良好混合。
发明内容
根据本发明的一方面，涡轮机包括压缩机、可操作地连接到压缩机的燃烧器、安装到燃烧器上的端盖和可操作地连接到燃烧器的喷嘴组件。该喷嘴组件包括具有延伸到第二表面的第一表面的帽状部件。该帽状部件还包括多个开口。多个束状微管组件可拆卸地安装在帽状部件的多个开口中的相应开口中。多个束状微管组件各包括具有第一端部和第二端部的主体部。流体室布置在主体部内，多个管在第一端部和第二端部之间延伸。多个管各包括流体式(fluidly)连接到流体室的至少一个开口。
根据本发明的另一方面，用于涡轮机的喷嘴组件包括帽状部件，其包括延伸到第二表面的第一表面和多个开口。该喷嘴组件还包括可拆卸地安装在帽状部件的多个开口中的相应开口中的多个束状微管组件。多个束状微管组件各包括具有第一端部和第二端部的主体部、布置在主体部内的流体室和在第一端部和第二端部之间延伸的多个管。多个管各包括流体式连接到流体室的至少一个开口。
根据本发明的又一方面，在包括帽状部件的喷嘴组件中形成可燃混合物的方法包括，将第一流体朝着可拆卸地安装在帽状部件中的多个束状微管组件引导。多个束状微管组件各包括具有第一端部和第二端部的主体部和延伸通过主体部的多个管。该方法还包括，使第一流体通过多个束状微管组件的各个中的多个管，以及将第二流体引导至布置在多个束状微管组件的各个中的流体室内。此外，该方法包括使第二流体从流体室进入多个束状微管组件的各个中的多个管内以形成燃料/空气混合物，以及将燃料/空气混合物从多个束状微管组件的各个排出至涡轮机燃烧器内。
这些优点及特征和其它优点及特征将通过以下结合附图的说明而变得更明显。
附图说明
视作本发明的主题在权利要求书中特别指出并清楚地声明。本发明的前述特征及优点和其它特征及优点通过以下结合附图的详细说明而显而易见，其中：
图1是包括根据本发明的示例性实施例构造的束状多管式喷嘴的示例性涡轮机的截面侧视图；
图2是图1的示例性涡轮机的燃烧器部分的截面图；
图3是根据本发明的示例性实施例构造的多个束状多管式喷嘴的截面图；
图4是图3的多个束状多管式喷嘴中的一个的详细截面图；
图5是根据本发明的一个示例性实施例的束状多管式喷嘴布置的正视图；
图6是根据本发明的另一个示例性实施例的束状多管式喷嘴布置的正视图。
通过参考附图，以下详细说明示例性地阐释了本发明的实施例以及优点和特征。
部件列表
2    涡轮机
4    压缩机
5    燃烧器组件
6    燃烧器
8    喷射组件壳体
10   涡轮
12   轴
22   扩散器
24   压缩机排出室
30   端盖
34   帽状部件
35   第一表面
36   第二表面
38   喷嘴组件
41   内部流动部分
44   燃烧器壳体
46   燃烧器衬套
48   燃烧室
49   环形燃烧室冷却通道
55   过渡件
62   第一级涡轮喷嘴
64   内壁
65   外壁
66   多个开口
68   环形通道
72   引导腔
90   束状微管组件
91   束状微管组件
92   束状微管组件
100  燃料进入管
101  燃料进入管
102  燃料进入管
112  主体部
113  第一端部
114  第二端部
115  多个微管
120  中心接收端口
124  内部燃料室
130  开口
134  开口
135  开口
150  单一环形阵列
175  中心束状微管组件
200  帽状部件
204  环形阵列
206  环形阵列
208  环形阵列
具体实施方式
在本申请中使用的术语“轴向的”和“轴向地”是指大致平行于燃烧管组件的中心体的中心纵向轴线延伸的方向和方位。在本申请中使用的术语“径向的”和“径向地”是指大致垂直于中心体的中心纵向轴线延伸的方向和方位。在本申请中使用的“上游”和“下游”是指相对于关于中心体中心纵向轴线的轴向流向的方向和方位。
首先参考图1，根据本发明的示例性实施例构造的涡轮机大体上表示为2。涡轮机2包括压缩机4和燃烧器组件5，该燃烧器组件5具有设有燃料喷嘴或喷射组件壳体8的至少一个燃烧器6。涡轮发动机2还包括涡轮10和共用的压缩机/涡轮轴12。在一个实施例中，燃气涡轮发动机2是PG9371 9FBA重载燃气涡轮发动机，其在商业上可从South Carolina，Greenville的通用电气公司获得。显然，本发明不局限于任何一种特定的发动机，并且可与其它燃气涡轮结合使用。
如图2最好地示出，燃烧器6与压缩机4和涡轮10流体连通式地联接。压缩机4包括彼此流体连通式地联接的扩散器22和压缩机排出室24。燃烧器6还包括位于其第一端的端盖30和帽状部件34。帽状部件34包括第一表面35和相对的第二表面36，以及多个开口，其中一个开口在图3中表示为37。帽状部件34与端盖30间隔开，以限定压缩空气所通过的内部流动路径41。如下文更全面地描述，帽状部件34限定喷嘴组件38的一部分。燃烧器6还包括燃烧器壳体44和燃烧器衬套46。如图所示，燃烧器衬套46从燃烧器壳体44向内径向地定位以限定燃烧室48。环形燃烧室冷却通道49限定在燃烧器壳体44和燃烧器衬套46之间。过渡件55将燃烧器6联接到涡轮10。过渡件55将在燃烧室48中产生的燃烧气体向下游地引向第一级涡轮喷嘴62。为此，过渡件55包括内壁64和外壁65。外壁65包括通向限定在内壁64和外壁65之间的环形通道68的多个开口66。内壁64限定在燃烧室48和涡轮10之间延伸的引导腔72。
在操作期间，空气流过压缩机4，压缩空气供应到燃烧器6，更具体地供应到喷射组件38，39和40。同时，燃料传送到喷射组件38，39和40以与空气混合并形成可燃混合物。当然，应理解的是，燃烧器6可包括额外的喷射组件(未示出)，并且涡轮机2可包括额外的燃烧器(未示出)。总之，可燃混合物被引导到燃烧室48并点燃以形成燃烧气体。然后，燃烧气体被引导到涡轮10。来自燃烧气体的热能转换成施加到驱动轴12上的机械旋转能。
更具体地，涡轮10通过轴12驱动压缩机4(如图1所示)。当压缩机4旋转时，压缩空气排出到扩散器22内，如相关箭头所示。在示例性实施例中，从压缩机4排出的大部分空气通过压缩机排出室24引向燃烧器6，剩余的压缩空气被引导以用于冷却发动机构件。更具体地，排出室24内的增压压缩空气经由外壁开口66引导进入过渡件55，并进入环形通道68。然后，空气从环形通道68引导通过环形燃烧室冷却通道49并到达喷嘴组件38-40。燃料和空气混合形成可燃混合物，该可燃混合物被点燃以在燃烧室48内形成燃烧气体。燃烧器壳体44便于使燃烧室48及其相关燃烧过程相对于诸如周围的涡轮构件的外部环境屏蔽。燃烧气体从燃烧室48引导通过引导腔72，并朝向涡轮喷嘴62。冲击第一级涡轮喷嘴62的热气产生最终生成来自涡轮2的功的旋转力。
在这一点上，应理解的是，上述构造用于更全面地理解涉及例如喷嘴组件38的特定结构的本发明的示例性实施例。如图3最好地示出，喷嘴组件38包括多个束状微管组件90-92，其可拆卸地安装在形成在帽状部件34内的开口37中。如下文更全面地描述，各束状微管组件90-92从自端盖30延伸通过内部流动路径41的相应燃料进入管100-102接收燃料。在这一点上，应理解的是，由于各束状微管组件90-91包括大致相同的结构，故随后给出关于束状微管组件90的详细说明，其中应理解束状微管91和92大致相似地构成。当然，在给定的系统内，束状微管组件可在尺寸、数量和各管内的燃料开口的数量和布置方面发生变化。
如图4最好地示出，束状微管组件90包括主体部112，其包括延伸到相对的第二端部114的第一端部113。束状微管组件还包括多个微管，其中一个表示为115。微管115使内部流动路径41和燃烧室48流体式地互连。此外，束状微管组件90包括通向内部燃料室124的中心接收端口120。在这一点上，应理解的是，仅仅示出和描述了一个内部燃料室，本发明的示例性实施例可包括多个燃料室。总之，中心接收端口120流体式连接到燃料进入管100。在所示的示例性实施例中，微管115围绕中心接收端口120布置。在这种布置中，燃料从燃料进入管100进入中心接收端口120。燃料填充内部燃料室124，并围绕多个微管115中的各个分布。根据本发明的一方面，各个微管115包括诸如130所表示的布置在帽状部件34的第二表面36附近的燃料进口。在这种构造中，以较短的间隔提供进入微管115的燃料，以与通过内部流动路径41的空气混合，以便于进入燃烧室48内的燃料和空气的贫油直接喷射(lean direct injection)。
根据本发明的其它方面，多个微管115各包括在第一端部113和第二端部114之间居中布置的开口134。该特定的构造便于将燃料和空气部分预混合地喷入燃烧室48内。根据本发明的又一示例性方面，多个微管115各包括布置在第一端部113附近的开口135，以便于将燃料和空气更完全预混合地喷入燃烧室48内。管115的长度和燃料开口的布置将基于改进的操作。此外，束状微管组件90可具有多于一个的燃料室，其在沿着多个微管115的不同轴向位置处带有多个燃料开口。
如图5最好地示出，束状微管组件90-92构成围绕中心束状微管组件175延伸的束状微管组件的整体环形阵列150的一部分。在这种布置，各束状微管组件可构造成相似的，或者以多种构造中的一种设置，例如贫油直接喷射，部分预混合的贫油直接喷射和完全预混合的贫油直接喷射，以控制特定燃烧器内的燃烧。相似地，如图6所示，喷射组件38可包括具有诸如表示为204，206和208的多个束状微管组件的同心环形阵列的帽状部件200。与上述方式相似，多个微管组件的各个可构造成相同的，或者以各种不同的构造设置，以控制特定燃烧管内的燃烧。在这一点上，应理解的是，本发明提供一种独特的喷嘴组件构造，其允许在单一帽状部件中采用具有相似的和/或不同的构造的多种喷嘴，以降低涡轮机的排放。
尽管通过结合仅仅有限数量的实施例详细描述了本发明，但是应当容易理解的是，本发明不局限于所公开的实施例。相反，本发明可改变以包括本文虽未说明但与本发明的范围和精神相一致的任何变化、变更、替换和等同布置。此外，尽管描述了本发明的许多实施例，但应当理解的是，本发明的方面可仅仅包括所述实施例的一些方面。因此，本发明不局限于前述说明，而仅由权利要求的范围所限制。

Claims (8)

1.一种涡轮机(2)，其包括：
压缩机(4)；
燃烧器(6)，其可操作地连接到所述压缩机(4)；
端盖(30)，其安装到所述燃烧器(6)上；和
喷嘴组件(38，39，40)，其可操作地连接到所述燃烧器(6)，
所述喷嘴组件(38，39，40)包括：
帽状部件(34)，其包括延伸到第二表面(36)的第一表面(35)和多个开口(37)，所述多个开口各延伸通过所述帽状部件(34)；以及
多个束状微管组件(90-92)，其可拆卸地安装在所述帽状部件(34)的多个开口(37)的相应开口中，所述多个束状微管组件(90-92)各包括具有第一端部(113)和第二端部(114)的主体部(112)、布置在所述主体部(112)内的流体室(124)和在所述第一端部(113)和所述第二端部(114)之间延伸的多个管(115)，所述多个管(115)各包括流体式连接到所述流体室(124)的至少一个开口(130，134，135)。
2.根据权利要求1所述的涡轮机(2)，其特征在于，所述多个束状微管组件(90-92)各包括中心接收端口(120)，所述中心接收端口(120)流体式连接到所述流体室(124)。
3.根据权利要求2所述的涡轮机(2)，其特征在于，所述喷嘴组件(38，39，40)包括多个流体管(100)，所述多个流体管(100)各在所述端盖(30)和位于所述多个束状微管组件(90-92)中的相应束状微管组件上的中心接收端口(120)之间延伸。
4.根据权利要求1所述的涡轮机(2)，其特征在于，各所述多个管(115)中的至少一个开口(130，134，135)形成在所述主体部(112)的第二端部(114)附近，以便于进入所述燃烧器的燃料和空气的贫油直接喷射。
5.根据权利要求1所述的涡轮机(2)，其特征在于，各所述多个管(115)中的至少一个开口(130，134，135)形成在所述主体部(112)的第一端部(113)附近，以便于获得燃料和空气的更完全预混合的混合物。
6.根据权利要求1所述的涡轮机(2)，其特征在于，各所述多个管(115)中的至少一个开口(130，134，135)大致居中地形成在所述主体部(112)内，以便于获得燃料和空气的部分预混合的混合物。
7.根据权利要求1所述的涡轮机(2)，其特征在于，所述多个束状微管组件(90-92)以围绕中心束状微管组件(175)周向延伸的环形阵列布置在所述帽状部件(34)上。
8.根据权利要求1所述的涡轮机(2)，其特征在于，所述多个束状微管组件(90-92)以多个同心环形阵列布置在所述帽状部件(34)上。
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US9140454B2 (en) 2015-09-22

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