CN106796031B - 火炬式点火器 - Google Patents

火炬式点火器 Download PDF

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CN106796031B
CN106796031B CN201580055696.0A CN201580055696A CN106796031B CN 106796031 B CN106796031 B CN 106796031B CN 201580055696 A CN201580055696 A CN 201580055696A CN 106796031 B CN106796031 B CN 106796031B
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combustion chamber
auxiliary
fuel injector
housing
mixing chamber
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CN106796031A (zh
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B.达姆
J.麦克科尔马克
E.彼得森
F.P.李
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Woodward Inc
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23Q—IGNITION; EXTINGUISHING-DEVICES
    • F23Q7/00—Incandescent ignition; Igniters using electrically-produced heat, e.g. lighters for cigarettes; Electrically-heated glowing plugs
    • F23Q7/06—Incandescent ignition; Igniters using electrically-produced heat, e.g. lighters for cigarettes; Electrically-heated glowing plugs structurally associated with fluid-fuel burners

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  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Abstract

一种燃气涡轮机燃烧器组件，其包括与主燃料喷射器和主空气入口流体连通的主燃烧室。火炬式点火器由主燃烧室承载，且包括辅助燃烧室壳体，其包括混合室和在混合室下游收缩的喉部区域。包括环绕辅助燃料喷射器的出口的多个旋流开口的空气旋流器靠近混合室联接到辅助燃烧室。点火源突出到辅助燃烧室的混合室中。

Description

火炬式点火器
要求优先权
本申请要求2014年8月18日提交的美国专利申请No.62/038,708的优先权，该申请的全部内容通过引用合并在本文中。
技术领域
本说明书大体涉及用于燃气涡轮发动机的燃烧器组件，其包含辅助火炬式点火系统以便于在主燃烧室中点火。
背景技术
对于许多高功率应用来说，燃气涡轮发动机是优选的内燃机种类。从根本上，燃气涡轮发动机特征在于联接到下游涡轮机的上游旋转压缩机和在其间的燃烧室。火炬式点火器是可用于点燃燃气涡轮发动机的主燃烧器的设备。在一些应用中，火炬式点火器相比常规的火花式点火器具有优势，这是因为火炬式点火器能够提供到主燃烧器的更大量的能量释放，且因此能够以更可靠的方式点燃发动机。为了实现这一点，火炬式点火器需要辅助的燃料和空气源，以及点火源。辅助空气流通常从发动机压缩机下游的压室获得；且辅助燃料从燃料计量单元或歧管获得。操作火炬式点火器的空气流要求可在不同条件下变化，但是通常小于主燃烧器的空气流要求。在典型的发动机上，像常规的火花式点火器那样，可以有两个火炬式点火器以备不时之需。
附图说明
图1是示例燃气涡轮发动机的半部、侧横截面视图。
图2A是第一示例火炬式点火器系统的半部、侧横截面视图。
图2B是在图2A中示出的火炬式点火器系统的径向空气旋流器的透视图。
图2C是图示通过操作在图2A中示出的火炬式点火器系统而实现的速度流场的图表。
图3A是第二示例火炬式点火器系统的半部、侧横截面视图。
图3B是在图3A中示出的火炬式点火器系统的轴向空气旋流器的透视图。
图3C是图示通过操作在图3A中示出的火炬式点火器系统而实现的速度流场的图表。
图4是包括联接到燃料喷射器的冷却空气子系统的火炬式点火器系统的半部、侧横截面视图。
图5是包括联接到燃料喷射器的冷却空气子系统的火炬式点火器系统的半部、侧横截面视图。
具体实施方式
在燃气涡轮发动机中，火炬式点火器点燃由发动机的燃烧器中的燃烧器喷嘴释放的燃料以产生加热的燃烧产物。加热的燃烧产物继而通过发动机的涡轮机膨胀以产生转矩。在更低的空气压降（ΔP）下（尤其在冷环境条件下），在主燃烧器喷嘴周围的可靠的点火和火焰传播可要求提供到操作包线的最小水平的能量。为了跨宽范围的操作条件提供能量，期望火炬式点火器系统的高品质的火焰稳定性/操作性。在特定方面，本公开涉及火炬式点火器系统，其例如通过合并径向和/或轴向空气旋流器部件而供应高能量，所述径向和/或轴向空气旋流器部件设计为在辅助燃烧室中产生强烈的再循环区域。在一些实施方式中，实现紊流和旋流部件的优化，以维持火炬式点火器火焰而不必保持点火源打开。在一些实施方式中，根据本公开的一个或多个实施例的火炬式点火器能够在火炬式燃烧器中提供由旋流稳定的燃烧增强的高能量释放，由此改善寒冷天气燃烧器熄火性能，且跨宽范围的操作条件提供可靠的再点火能力。在一些实施方式中，根据一个或多个实施例的火炬式点火器可在火炬式燃烧器内部提供近化学计量燃烧过程。这种燃烧过程可产生更高的燃气温度和痕量化学活性物质，其对于在主燃烧室（例如，燃烧器拱顶（dome）106）中的点火来说是有益的。通过近化学计量燃烧过程实现的潜在的益处是在主燃烧室内改善的火焰传播和在燃烧器启动期间更少的排烟。
图1是示例燃气涡轮发动机10的半部、侧横截面视图。燃气涡轮发动机10是涡轮喷气式燃气涡轮机，其可例如用于驱动喷气式飞机。然而，应当理解，在本公开中描述的构思不因此受限，且能够合并在各种其他类型的燃气涡轮发动机（例如，涡轮风扇发动机、涡轮螺桨发动机、涡轮轴发动机或工业/船用发动机）的设计中。
如图所示，燃气涡轮发动机10大体促进连续的轴向气体流。也就是说，气体大体沿由图1中的箭头指示的轴向下游方向流动通过发动机10。燃气涡轮发动机10包括入口12，其接收环境空气14且将环境空气引导到压缩机16。环境空气14被抽吸通过压缩机16的多个级。离开压缩机16的高压空气18被引入到燃烧器100。在特定情形中，燃烧器100是环绕发动机的主轴20的环状燃烧器，或者关于轴径向朝外定位的罐式燃烧器。
燃烧器100包括燃烧护罩102、多个燃料喷射器104、燃烧器拱顶106和火炬式点火器系统108。在燃烧器100处，高压空气18与液体烃燃料（未示出）混合，且被火炬式点火器系统108点燃以产生加热的燃烧产物22。燃烧产物22传递通过涡轮机24的多个级。涡轮机24从高压、高温燃烧产物22中提取能量。由涡轮机24从燃烧产物22中提取的能量驱动压缩机16，该压缩机16通过主轴20联接到涡轮机。离开涡轮机24的排气26通过排出喷嘴28加速进入大气中，以提供推力或推进动力。
图2A-图2C示出能够在图1的火炬式点火器系统108中使用的示例火炬式点火器200。在特定情形中，火炬式点火器系统108包括多个、间隔开的火炬式点火器。火炬式点火器200具有外部壳体201，该外部壳体201具有内部室203；内部室203在图1中示出为基本上柱形。外部壳体201在内部接收辅助燃烧室壳体205，从而限定在它们之间的环状空气通路207。辅助燃烧室壳体205邻接内部室203的上端。环状空气通路207包括朝主燃烧室开口的入口209。在图1中同样示出为基本上柱形的辅助燃烧室壳体205限定内部辅助燃烧室202。又示出为柱形的径向空气旋流器204联接到辅助燃烧室壳体205的上端。诸如火花生成点火器的点火源206延伸通过辅助燃烧室202的侧壁而设置。
辅助燃烧室壳体205示出为限定柱形混合室208、和缩颈的喉部区域210，所述喉部区域210示出为锥形，在混合室208的下游收缩到喷嘴管道211。锥形的角度能够在不同的情形中不同。在特定情形中，喉部区域210能够突然收缩，从而在混合室208的较大直径与喉部区域210的较小直径之间形成肩部或台阶，其中，肩部或台阶垂直于辅助燃烧室壳体205的纵向轴线。在一些实施例中，点火源206在辅助燃料喷射器214的出口的下游处径向突出到辅助燃烧室202的混合室208中。辅助燃料喷射器214定位在辅助燃烧室202的顶部处，其中，其出口轴向地定向成与辅助燃烧室202的中心轴线一致地注射燃料。点火源206在辅助燃烧室202中点燃从辅助燃料喷射器214输出的燃料，且收缩的喉部区域210和喷嘴管道211将流动从辅助燃烧室202喷出以在主燃烧室中产生火焰喷射。所得到的火焰喷射深入到主燃烧室中，且提供强的（高热能的）、高表面积的火焰，以在主燃烧室中燃烧空气和燃料混合物。
径向空气旋流器204示出为具有多个旋流开口212，其邻近辅助燃烧室壳体205的上端且环绕辅助燃料喷射器214的出口延伸通过旋流器204的侧壁。空气旋流器204的旋流开口212将环状空气通路207与辅助燃烧室202的混合室208流体连接，以促进空气流通过火炬式点火器200。旋流开口212是成角度的，大体径向定向，沿着跨辅助燃烧室壳体205的弦定向，以使得从环状空气通路207入射到辅助燃烧室202中的空气打旋，从而沿着辅助燃烧室202的纵向轴线形成流动漩涡。可提供比示出的旋流开口更少或更多的旋流开口212。在特定情形中，空气旋流器204能够具有与混合室208不同的直径，且能够以锥形或者利用陡峭的肩部或台阶从所述不同的直径过渡。例如，从空气旋流器204到混合室208的直径增加的台阶能够促进在邻近台阶的区域中的紊流。
图3A-图3C的火炬式点火器300类似于火炬式点火器200，除了其具有轴向空气旋流器304的特征外。如图所示(参见图3B)，轴向空气旋流器304是盘形的，且联接到辅助燃烧室壳体305的上端，与内部室203的上端间隔开。轴向空气旋流器304包括通过其的多个旋流开口312，其以周向图案设置，环绕辅助燃料喷射器214的出口，且大体轴向地定向，相对于辅助燃烧室202和辅助燃料喷射器214的纵向轴线成非零角度。旋流开口312设置成沿着辅助燃烧室202的纵向轴线形成流动漩涡。可提供比示出的旋流开口更少或更多的旋流开口212。在特定情形中，混合室208的上端能够具有与混合室208的剩余部分不同的直径，类似地。
旋流开口212、312的流动面积、定向和数目以及辅助燃烧室202的形状被设计大小，例如迭代地使用计算流体动力学软件，以在混合室208中在辅助燃料喷射器214的出口附近产生再循环区域。再循环空气/燃料流215在图2C和图3C中由速度场流线示出为在辅助燃料喷射器214的出口周围呈大体环形，朝下（远离燃料喷射器214的出口）流动通过辅助燃烧室202的中心并沿着内部侧壁朝上（向后朝燃料喷射器214的出口）流动。环形的再循环215从混合室208的顶端到混合室208的底端（喉部区域210的缩颈部开端附近）延伸过混合室208的整个轴向长度。从混合室208到喉部区域210的缩颈部有助于形成再循环流215，因为遭遇缩颈部和减少的流动面积的周向流沿着侧壁向上被向后再引导。一旦由点火源206点燃，在再循环区域中所得到的紊流和再循环就保持来自辅助燃料喷射器214的燃料的燃烧，而不必维持点火源206打开，这是因为点燃的空气/燃料的一部分向后再循环到来自辅助燃料喷射器214的入射燃料中。而且，紊流和再循环倾向于将燃烧的空气/燃料与未燃烧的空气/燃料混合，倾向于贯穿辅助燃烧室202更均匀地点燃空气/燃料，且产生更强、更高能量的燃烧。
在特定情形中，如果火炬式点火器系统以间歇方式操作（例如，反复的开/关循环），则在关闭期间，因不流动的燃料导致的积碳能够限制在辅助燃料喷射器中的燃料流通路。由于更低的燃料流速率所要求的更小的通路，这种影响能够更显著。因此，在一些实施方式中，在火炬关闭的那些时间期间，需要吹扫或冷却燃料喷射器。火炬式点火器系统的一些实施例能够包括被设计为以很少的额外硬件或者不用额外硬件提供辅助燃料喷射器的吹扫和冷却。
图4是诸如火炬式点火器200或300的火炬式点火器的上端600的半部、侧横截面视图，其包括围绕辅助燃料喷射器214的冷却空气子系统602。在该实施例中，来自涡轮发动机的主压缩机的空气行进通过浸没在相对冷的管道空气（即，不源自发动机内的新鲜空气）中的通路。冷却管道空气流入外部火炬式点火器壳体201中且通过子系统602的导管603进入在壳体201和辅助燃料喷射器214之间的环状间隙604中，之后离开进入辅助燃烧室202中。
图5是诸如火炬式点火器200或300的火炬式点火器的上端700的半部、侧横截面视图，其包括联接到辅助燃料喷射器214的吹扫空气子系统。在该示例中，冷却管道空气流动通过导管703进入辅助燃料喷射器214的孔702中。在导管703中的止回阀704调节空气流，使得当燃料压力减少到规定水平时（例如，当火炬式点火器系统停用时），由于净压力差，吹扫空气开始流动通过燃料回路。
已经描述了本发明的多个实施例。然而，将理解，在不脱离本发明的精神和范围的情况下，可进行各种修改。

Claims (4)

1.一种燃气涡轮机燃烧器组件，包括：
主燃烧室(106)，其与主燃料喷射器(104)和主空气入口流体连通；和
火炬式点火器(108,200,300)，其由所述主燃烧室承载，包括：
辅助燃烧室壳体(205,305)，其包括柱形混合室(208)和锥形缩颈的喉部区域(210)，所述喉部区域与所述混合室同轴地对准并且所述喉部区域在所述混合室下游收缩；
空气旋流器(204,304)，其包括环绕辅助燃料喷射器(214)的出口的多个旋流开口(212,312)，所述空气旋流器靠近所述混合室而联接到所述辅助燃烧室壳体；和
点火源(206)，其在所述辅助燃料喷射器下游的位置处径向地通过所述辅助燃烧室壳体的所述混合室的侧壁而突出；
其中所述辅助燃烧室壳体(205,305)的所述混合室和所述喉部区域配置成在所述辅助燃烧室壳体内部中产生再循环流，这是因为遭遇所述喉部区域的流体沿着所述侧壁被再引导，所述再循环流具有围绕所述辅助燃料喷射器的所述出口的大体环形形状，该再循环流远离所述辅助燃料喷射器地流动通过所述辅助燃烧室壳体(205,305)的所述内部中的中心区域，且朝所述辅助燃料喷射器沿着所述辅助燃烧室壳体的所述侧壁流动。
2.根据权利要求1所述的燃气涡轮机燃烧器组件，其特征在于，所述多个旋流开口(212)包括相对于所述辅助燃料喷射器(214)的所述出口径向定向的周向图案的空气开口。
3.根据权利要求1所述的燃气涡轮机燃烧器组件，其特征在于，所述辅助燃料喷射器(214)的所述出口和所述多个旋流开口(212,312)定位在所述点火源(206)的上游。
4.根据权利要求1所述的燃气涡轮机燃烧器组件，其特征在于：
所述火炬式点火器包括外部火炬式点火器壳体(201)，其联接到所述主燃烧室(106)且在内部接收所述辅助燃烧室壳体(205,305)，所述外部火炬式点火器壳体和所述辅助燃烧室壳体在其间限定环状空气通路(207)，该环状空气通路具有朝所述主燃烧室开口的空气入口(209)；并且
其中，所述多个旋流开口(212,312)将所述环状空气通路和所述混合室(208)流体连接。
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US20160047318A1 (en) 2016-02-18
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CN106796031A (zh) 2017-05-31
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