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公开(公告)号：US5694764A
公开(公告)日：1997-12-09
申请号：US529930
申请日：1995-09-18
申请人： Edward S. Blain , Tim Sullivan , Stuart A. Greenwood , Michael W. Sledd , Kent Weber , Robert L. Bracken
发明人： Edward S. Blain , Tim Sullivan , Stuart A. Greenwood , Michael W. Sledd , Kent Weber , Robert L. Bracken
摘要： An engine is provided having a fuel supply system which includes apparatus of straightforward construction that is powered solely by a flow of fuel through a delivery line to the engine for increasing the flow of fuel through the delivery line to the engine during start-up of the engine. A small control volume of pressurized fuel is stored during a preceding operational period of the engine for use in augmenting the fuel flow to the engine during a subsequent start-up of the engine. A converter apparatus is also disclosed for converting a portion of the fuel flow from the control volume and/or from a main fuel pump into an increased flow rate or pressure of fuel to the engine during the subsequent start-up. The control volume of fuel is stored in such a manner that volume compensation for changes in ambient temperature is provided, and in such a manner that the fuel line is positively shut off during periods of inoperation such that the fuel cannot leak out or evaporate and thus not be available for rapid start-up of the engine during a subsequent start.
摘要翻译： 提供一种具有燃料供应系统的发动机，该燃料供应系统包括直接构造的装置，该装置仅由燃料流通过输送管道供给发动机，以在燃料的启动期间增加燃料通过输送管线到发动机的流量 发动机。 在发动机的前一操作期间存储小的控制量的加压燃料，以用于在随后的发动机起动期间增大燃油流向发动机。 还公开了一种转换器装置，用于在随后的启动期间将来自控制容积和/或主燃料泵的燃料流的一部分转换成增加的燃料流向发动机的流量或压力。 燃料的控制体积以对环境温度变化进行体积补偿的方式进行存储，并且以这样的方式使燃料管线在操作期间被正确关闭，使得燃料不会泄漏或蒸发，因此 在随后的启动期间不能用于发动机的快速启动。
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公开(公告)号：US5063745A
公开(公告)日：1991-11-12
申请号：US379548
申请日：1989-07-13
CPC分类号： F23D11/005 , F23R3/28
摘要： Improved fuel atomization for turbine engines operating at low fuel flows and at high altitudes is accomplished in an engine 10 having an annular combustor 12 by utilizing fuel injectors 18 provided with fuel supply tubes 24 disposed within air tubes 20 wherein the fuel supply tubes 24 each have an exit orifice 26 internally of the corresponding air tube 20 and upstream of an exit orifice 22 thereof with a fuel impingement surface 28 being provided within the air tube 20 in confronting relation to the exit orifice 26 of the fuel supply tube 24 to produce a conical fuel film 36 subjected to pressurized air to enhance fuel atomization.
摘要翻译： 在具有环形燃烧器12的发动机10中，通过利用设置有设置在空气管20内的燃料供给管24的燃料喷射器18，在具有环形燃烧器12的发动机10中实现改进的燃料雾化，其中燃料供应管24各自具有 在对应的空气管20内部的出口孔26和其出口孔22的上游，燃料冲击表面28以与燃料供应管24的出口孔26相对的方式设置在空气管20内，以产生锥形 经受加压空气的燃料膜36以增强燃料雾化。
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公开(公告)号：US5321950A
公开(公告)日：1994-06-21
申请号：US773549
申请日：1991-10-09
CPC分类号： F02C7/264 , F02C7/2365 , F23D11/104 , F23D11/106 , F05D2220/50 , F05D2260/601
摘要： In order to achieve ignition at altitude, particularly in relatively small combustors (10) with low fuel flow rates, a fuel injection system (20) includes an air nozzle (26), a fuel nozzle (28), and an air assist tube (34). The fuel nozzle (28) is disposed in a manner so as to direct fuel through the air nozzle (26) and includes a fuel metering orifice (30) or capillary tube (32) to control fuel flow therethrough. The air assist tube (34) is integrally associated with the fuel nozzle (28) downstream of the fuel metering orifice (30) or capillary tube (32) to accelerate fuel flowing through the fuel nozzle (28). With this arrangement, the air nozzle (26) may comprise an opening in a combustor wall (14) defining a combustion chamber (12) of a turbine engine combustor (10) wherein a combustor case (16) surrounds the combustor wall (14) to define an air flow path 18 in communication with a compressed air source whereby compressed air flows through the opening (26) and into the combustor (10) along with fuel from the fuel nozzle (28) and air from the air assist tube (34).
摘要翻译： 为了在高度上实现点火，特别是在具有低燃料流量的相对小的燃烧器（10）中，燃料喷射系统（20）包括空气喷嘴（26），燃料喷嘴（28）和空气辅助管 34）。 燃料喷嘴（28）以使得燃料通过空气喷嘴（26）的方式设置并且包括燃料计量孔（30）或毛细管（32）以控制通过其中的燃料流动。 空气辅助管（34）与燃料喷嘴（28）在燃料计量孔（30）或毛细管（32）下游一体地相关联，以加速流过燃料喷嘴（28）的燃料。 利用这种布置，空气喷嘴（26）可以包括限定涡轮发动机燃烧器（10）的燃烧室（12）的燃烧器壁（14）中的开口，其中燃烧器壳体（16）围绕燃烧器壁（14） 以限定与压缩空气源连通的空气流动路径18，由此压缩空气与来自燃料喷嘴（28）的燃料和来自空气辅助管（34）的空气一起流过开口（26）并进入燃烧器（10） ）。
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4.发明授权Tangentially directed air assisted fuel injection and small annular combustors for turbines 失效切向定向空气辅助燃料喷射和小型涡轮机环形燃烧器
公开(公告)号：US5317864A
公开(公告)日：1994-06-07
申请号：US954971
申请日：1992-09-30
CPC分类号： F23R3/50 , F23R3/045 , F23R3/28 , F05B2220/50 , F05B2250/322 , Y02T50/675
摘要： Difficulties in downsizing annular combustors (20) due to orienting fuel injectors with respect to oxidant blast tubes are avoided in a construction for a combustor (20) including radially spaced annular walls (22, 24) and an interconnecting radial wall (26) defining an annular combustion chamber (32). A plurality of circumferentially spaced tubes (28, 30) extend through the radially outermost annular wall (24) and are directed generally tangentially into the combustion space (32). A plurality of fuel injectors (42) are provided for directing fuel radially inwardly into the space (32) and are circumferentially spaced about the combustion space (32) and located between the tubes (28).
摘要翻译： 在包括径向隔开的环形壁（22,24）和相互连接的径向壁（26）的燃烧器（20）的结构中避免了因相对于氧化剂鼓风管定向燃料喷射器来减小环形燃烧器（20）的难度， 环形燃烧室（32）。 多个周向间隔开的管（28,30）延伸穿过径向最外面的环形壁（24），并且大致切向地指向燃烧空间（32）。 设置多个燃料喷射器（42），用于将燃料径向向内引导到空间（32）中，并且围绕燃烧空间（32）周向间隔开并且位于管（28）之间。
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公开(公告)号：US5097666A
公开(公告)日：1992-03-24
申请号：US448541
申请日：1989-12-11
CPC分类号： F02C7/264 , F02C7/2365 , F23D11/104 , F23D11/106 , F05D2220/50 , F05D2260/601
摘要： In order to achieve ignition at altitude, particularly in relatively small combustors (10) with low fuel flow rates, a fuel injection system (20) includes an air nozzle (26), a fuel nozzle (28), and an air assist tube (34). The fuel nozzle (28) is disposed in a manner so as to direct fuel through the air nozzle (26) and includes a fuel metering orifice (30) or capillary tube (32) to control fuel flow therethrough. The air assist tube (34) is integrally associated with the fuel nozzle (28) downstream of the fuel metering orifice (30) or capillary tube (32) to accelerate fuel flowing through the fuel nozzle (28). With this arrangement, the air nozzle (26) may comprise an opening in a combustor wall (14) defining a combustion chamber (12) of a turbine engine combustor (10) wherein a combustor case (16) surrounds the combustor wall (14) to define an air flow path 18 in communication with a compressed air source whereby compressed air flows through the opening (26) and into the combustor (10) along with fuel from the fuel nozzle (28) and air from the air assist tube (34).
摘要翻译： 为了在高度上实现点火，特别是在具有低燃料流量的相对较小的燃烧器（10）中，燃料喷射系统（20）包括空气喷嘴（26），燃料喷嘴（28）和空气辅助管 34）。 燃料喷嘴（28）以使得燃料通过空气喷嘴（26）的方式设置并且包括燃料计量孔（30）或毛细管（32）以控制通过其中的燃料流动。 空气辅助管（34）与燃料喷嘴（28）在燃料计量孔（30）或毛细管（32）下游一体地相关联，以加速流过燃料喷嘴（28）的燃料。 利用这种布置，空气喷嘴（26）可以包括限定涡轮发动机燃烧器（10）的燃烧室（12）的燃烧器壁（14）中的开口，其中燃烧器壳体（16）围绕燃烧器壁（14） 以限定与压缩空气源连通的空气流动路径18，由此压缩空气与来自燃料喷嘴（28）的燃料和来自空气辅助管（34）的空气一起流过开口（26）并进入燃烧器（10） ）。
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公开(公告)号：US5027603A
公开(公告)日：1991-07-02
申请号：US583007
申请日：1990-09-14
摘要： Improved fuel atomization for turbine engines operating at low fuel flows and at high altitudes is accomplished in an engine having an annular combustor 26 by utilizing start fuel injectors 46 provided with discharge orifices 56 and planar impingement surfaces 60 within the path of fuel discharged from the orifices 56 to provide flat sprays 62 that are generally tangential to the annular combustor 26 so as to be intercepted by an igniter 70 in a radial wall 34 of the combustor 26.
摘要翻译： 在具有环形燃烧器26的发动机中，通过利用在喷嘴排出的燃料的路径内设置有排放孔56和平面冲击表面60的起动燃料喷射器46，在具有环形燃烧器26的发动机中实现用于在低燃料流动和高海拔地区运行的涡轮发动机的改进的燃料雾化。 以提供平坦的喷雾62，其通常与环形燃烧器26相切，以便被燃烧器26的径向壁34中的点火器70拦截。
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公开(公告)号：US5277022A
公开(公告)日：1994-01-11
申请号：US966903
申请日：1992-10-23
CPC分类号： F23R3/045 , F23R3/32 , F23R3/54 , F05B2220/50
摘要： In order to enhance fuel injection efficiency, and particularly to atomize low fuel flows at high velocity with low fuel pressure, a fuel injection system 24 for a combustor 22 of a turbine engine 20 has an air blast tube 48 and a fuel supply tube 76. The air blast tube 48 is mounted at an acute angle relative to a wall 26 of the combustor 22 and has a first end 50 in communication with the combustor 22 and a second, enlarged end 52 disposed at an acute angle to an axis 54 of the air blast tube 48 in communication with a source of compressed air externally of the wall 26 of the combustor 22. The air blast tube 48 is operable to deliver compressed air from the source into the combustor 22. The fuel supply tube 76 delivers fuel through a fuel supply orifice 58 to a point at or near the first end 50 of the air blast tube 48 and has a first end 60 in communication with the combustor 22 through the fuel supply orifice 58 and a second end 62 in communication with a source of fuel externally of the wall 26 of the combustor 22. With this arrangement, the fuel supply tube 76 extends to a point communicating internally with the air blast tube 48 but adjacent a discharge opening 64 of the air blast tube 48 to produce an enhanced atomized fuel/air mixture thereby.
摘要翻译： 为了提高燃料喷射效率，特别是以低燃料压力高速喷雾低燃料流量，用于涡轮发动机20的燃烧器22的燃料喷射系统24具有鼓风管48和燃料供给管76。 鼓风管48相对于燃烧器22的壁26成锐角地安装，并且具有与燃烧器22连通的第一端部50和与第二端部52成直角的第二扩大端部52。 空气鼓风管48与燃烧器22的壁26外部的压缩空气源连通。鼓风管48可操作以将压缩空气从源输送到燃烧器22中。燃料供应管76将燃料通过 燃料供应孔58连接到空气鼓风管48的第一端50处或其附近，并且具有通过燃料供应孔58与燃烧器22连通的第一端60和与燃料源58连通的第二端62 外部 通过这种布置，燃料供应管76延伸到与鼓风管48内部连通但与鼓风管48的排放口64相邻的点，以产生增强的雾化燃料/空气 混合物。
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公开(公告)号：US5220794A
公开(公告)日：1993-06-22
申请号：US542739
申请日：1990-06-22
摘要： The high cost of fuel injection nozzles for a gas turbine engine may be reduced by utilizing nozzles (60) formed of simple tubes (63) of capillary cross section having an integral flange (62) formed on one end (86) thereof.
摘要翻译： 用于燃气涡轮发动机的燃料喷射喷嘴的高成本可以通过利用由具有形成在其一端（86）上的整体凸缘（62）的毛细管横截面的简单管（63）形成的喷嘴（60）来减少。
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公开(公告)号：US5140807A
公开(公告)日：1992-08-25
申请号：US649478
申请日：1991-02-01
摘要： Poor atomization of fuel at low fuel flows in a gas turbine engine may be overcome in an engine including a rotary compressor (14), a turbine wheel (22) coupled to the compressor (14) to drive the same and a nozzle of (26) for directing gases of combustion at the turbine wheel (22). An annular combustor (34) defines a combustion annulus about the turbine wheel (22) and has an outlet (30) connected to the nozzle (26). A plurality of air blast tubes (50) include exit openings (52) circumferentially spaced about the combustor (32) and each has an axis (54) that is generally circumferentially directed with respect to the combustion annulus. A fuel discharge orifice (64) is located within each air blast tube (50) and a flange (66) is aligned with each orifice (64) in the path of fuel being discharged therefrom and at a substantial acute angle (.theta.) to the axis (54).
摘要翻译： 在燃气涡轮发动机中的低燃料流动下的燃料雾化不良可以在包括旋转式压缩机（14），联接到压缩机（14）以驱动其的涡轮机叶轮（22）和（26）的喷嘴的发动机中克服 ），用于在涡轮机叶轮（22）处引导燃烧气体。 环形燃烧器（34）围绕涡轮机叶轮（22）限定燃烧环，并且具有连接到喷嘴（26）的出口（30）。 多个鼓风管（50）包括围绕燃烧器（32）周向间隔开的出口（52），并且每个具有相对于燃烧环通常周向定向的轴线（54）。 燃料排放孔（64）位于每个鼓风管（50）内，并且法兰（66）与燃料路径中的每个孔（64）对准，并且以相当于锐角 轴（54）。
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