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    Turbine engine with airblast injection
    4.
    发明授权
    Turbine engine with airblast injection 失效
    涡轮发动机与喷气注射

    公开(公告)号：US5263316A

    公开(公告)日：1993-11-23

    申请号：US455508

    申请日：1989-12-21

    申请人： Jack R. Shekleton

    发明人： Jack R. Shekleton

    IPC分类号： F02G1/00 ,  F23D11/10 ,  F23R3/04 ,  F23R3/28

    CPC分类号： F02G1/00 ,  F23D11/108 ,  F23R3/045 ,  F23R3/28

    摘要： Improved fuel atomization for turbine engines utilizing high viscosity fuels is accomplished in an engine having an annular combustor (26) by providing an air injector (52) which produces an air stream (50) generally tangentially directed into the combustor (26) to intersect a fuel spray or film (46) also generally tangentially directed into the combustor (26) by a fuel injector (48) to atomize fuel for ignition by an igniter (60) in an annular outer wall (34) of the combustor (26).

    摘要翻译： 利用高粘度燃料的涡轮发动机的改进的燃料雾化在具有环形燃烧器（26）的发动机中通过提供空气喷射器（52）来实现，空气喷射器（52）产生大致切向地引导到燃烧器（26）中的空气流 燃料喷雾或薄膜（46）也通过燃料喷射器（48）大致相切地引导到燃烧器（26）中，以通过燃烧器（26）的环形外壁（34）中的点火器（60）来雾化燃料。

    Tangential air blast impingement fuel injected combustor
    5.
    发明授权
    Tangential air blast impingement fuel injected combustor 失效
    切向空气喷射冲击燃料喷射燃烧器

    公开(公告)号：US5233825A

    公开(公告)日：1993-08-10

    申请号：US652008

    申请日：1991-02-07

    申请人： Jack R. Shekleton

    发明人： Jack R. Shekleton

    IPC分类号： F02C7/236 ,  F23D11/10

    CPC分类号： F23D11/108 ,  F02C7/2365 ,  F05D2220/50 ,  F05D2250/322

    摘要： In order to efficiently atomize a fuel/air mixture to reduce smoke, a fuel injection system (26) for a combustor (12) of a turbine engine (10) includes an air blast tube (16), a fuel supply passage (42), and an impingement surface (30). The air blast tube (16) is mounted in relation to an opening (18) in a wall (20) of the combustor (12) such that a first end (22) of the tube (16) is in communication with the combustor (12) and a second end (24) of the tube (16) is in communication with a source of compressed air externally of the combustor (12) to facilitate the delivery of compressed air from the source into the combustor (12). The fuel supply passage (42) is adapted to deliver fuel to a fuel supply orifice (28) by having a first end (34) in communication with the combustor (12) through the fuel supply orifice (28) and a second end ( 36) in communication with a source of fuel externally of the combustor (12) with the fuel supply orifice (28) being disposed externally of but adjacent to the air blast tube (16). The impingement surface (30) is positioned in the path of fuel discharged from the fuel supply orifice (28) to produce a fuel spray directed into the path of compressed air discharged from the air blast tube (16) at a point externally of the air blast tube (16) for producing an interaction of the fuel spray and compressed air within the combustor (12). With the unique arrangement of the air blast tube (16) and fuel supply passage (42), the fuel injection system (26) is particularly well suited for producing an atomized fuel/air mixture in an efficient smoke-reducing manner.

    摘要翻译： 为了有效地雾化燃料/空气混合物以减少烟雾，用于涡轮发动机（10）的燃烧器（12）的燃料喷射系统（26）包括鼓风管（16），燃料供给通道（42） ，和冲击表面（30）。 风管（16）相对于燃烧器（12）的壁（20）中的开口（18）安装，使得管（16）的第一端（22）与燃烧器（16）连通 12）和管（16）的第二端（24）与燃烧器（12）外部的压缩空气源连通，以便于将压缩空气从源输送到燃烧器（12）中。 燃料供给通道（42）适于通过具有通过燃料供给孔（28）与燃烧器（12）连通的第一端（34）和第二端（36）将燃料输送到燃料供给孔（28） ）与燃烧器（12）外部的燃料源连通，燃料供给孔（28）设置在鼓风管（16）的外部但邻近于鼓风管（16）。 冲击表面（30）位于从燃料供给孔（28）排出的燃料的路径中，以产生一个燃料喷雾，该燃料喷雾引导到空气鼓风管（16）的空气在空气外部的位置排出的压缩空气的路径 用于产生燃烧器（12）内的燃料喷雾和压缩空气的相互作用的鼓风管（16）。 由于空气鼓风管16和燃料供给通路42的独特配置，燃料喷射系统26特别适用于以有效的减烟方式生产雾化的燃料/空气混合物。

    Liquid atomizing devices
    6.
    发明授权
    Liquid atomizing devices 失效
    液体成型装置

    公开(公告)号：US3799449A

    公开(公告)日：1974-03-26

    申请号：US30311872

    申请日：1972-11-02

    申请人： LUCAS AEROSPACE LTD

    发明人： GARDNER S

    IPC分类号： B05B1/34 ,  F23D11/10 ,  F23D11/38 ,  B05B7/06

    CPC分类号： F23D11/108

    摘要： A liquid atomizing device which can be inserted into an air tube within a ring of air swirler blade includes a first tubular body having an outwardly flared open end. A second tubular body is located in the first tubular body so as to form an intermediate air passage. A shell member attached to the second tubular body is disposed within the outwardly flared end and has an outwardly flared frusto-conical portion. The shell member has an inwardly directed annular lip upstream of the frusto-conical portion. An end wall of the second tubular body has a series of inclined nozzle openings therein to direct liquid passing therethrough onto the shell member. The liquid passes around the annular lip and mixes with air from the air passage downstream of the frustoconical portion.

    摘要翻译： 可以插入到空气旋流器叶片环内的空气管中的液体雾化装置包括具有向外张开的开口端的第一管状体。 第二管状体位于第一管状体中以形成中间空气通道。 附接到第二管状体的壳体构件设置在向外扩张的端部内并具有向外张开的截头圆锥形部分。 外壳构件在截头圆锥形部分的上游具有向内指向的环形唇缘。 第二管状体的端壁在其中具有一系列倾斜的喷嘴开口，以将穿过其中的液体引导到壳构件上。 液体通过环形唇缘并与来自截头圆锥形部分下游的空气通道的空气混合。

    AIR DIRECTED FUEL INJECTION
    10.
    发明申请
    AIR DIRECTED FUEL INJECTION 有权
    空气指导燃油注射

    公开(公告)号：US20150316265A1

    公开(公告)日：2015-11-05

    申请号：US14650304

    申请日：2013-11-11

    申请人： Siemens Aktiengesellschaft

    发明人： Timothy DOLMANSLEY

    IPC分类号： F23R3/28

    CPC分类号： F23R3/28 ,  F23D11/108 ,  F23D11/24 ,  F23Q9/00 ,  F23R3/04 ,  F23R3/343

    摘要： A combustion chamber for a gas turbine is provided. The combustion chamber has a pilot burner device, a fuel injector, an ignitor unit and an air blast injector. The pilot burner device has a pilot body with a pilot surface facing an inner volume of the combustion chamber. The fuel injector has a fuel outlet for injecting a fuel into the inner volume, wherein the fuel outlet is arranged at the pilot surface. The ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable. The air blast injector is adapted for injecting an air blast into the inner volume, wherein the air blast injector includes an air blast outlet arranged at the pilot surface such that the air blast is injectable in the direction to the fuel outlet and the ignitor unit for directing the fuel to the ignitor unit.

    摘要翻译： 提供了一种用于燃气轮机的燃烧室。 燃烧室具有引燃燃烧器装置，燃料喷射器，点火器单元和鼓风喷射器。 导向燃烧器装置具有引导体，其具有面向燃烧室的内部容积的先导表面。 燃料喷射器具有用于将燃料喷射到内部容积中的燃料出口，其中燃料出口布置在导向面上。 点火器单元布置在导向表面处，使得通过点火器单元的燃料是可燃的。 喷气喷射器适用于将空气吹入喷射到内部容积中，其中喷气喷射器包括布置在飞行员表面处的鼓风出口，使得气流可以沿着燃料出口和点火器单元注入， 将燃料引导到点火器单元。