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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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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：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：US5261224A
公开(公告)日：1993-11-16
申请号：US970101
申请日：1992-11-02
摘要： Difficulties in achieving reliable starts in gas turbine engines operating at high altitude are avoided in a gas turbine engine including a rotary compressor (10), a rotary turbine wheel (12) coupled to the compressor (10) to drive the same, and a nozzle (42) for directing gases of combustion against the turbine wheel (12). An annular combustor (34) has an outlet (40) connected to the nozzle (42) and an opposed dome (38) that is axially spaced from the outlet (40). At least three sets of air injection openings (80, 92, 100) are axially spaced from one another with one set (82) in close proximity to the dome (38). Fuel injectors (86, 94) are associated with two of the sets (80, 92, 100), including the one set (80) and another of the sets (92) that is nearest the one set (80). The air injection openings of the sets (80 and 92) and the fuel injectors (86, 94) are constructed, arranged and sized so that the air/fuel ratio of air injected by each of the sets (80, 92) is no more than about 5/1 and the remaining set of air injection openings (100) is constructed, arranged and sized so that the total air/fuel ratio of air and fuel through all of the sets (80, 92, 100) and fuel injectors (86, 94) is approximately stoichiometric.
摘要翻译： 在包括旋转式压缩机（10），联接到压缩机（10）的旋转涡轮机叶轮（12）以驱动旋转式压缩机（10）的燃气涡轮发动机中，避免了在高空作业的燃气涡轮发动机中实现可靠启动的困难，以及喷嘴 （42），用于将燃烧气体引导到涡轮机叶轮（12）。 环形燃烧器（34）具有连接到喷嘴（42）的出口（40）和与出口（40）轴向间隔开的相对的圆顶（38）。 至少三组空气喷射开口（80,92,100）彼此轴向间隔开，一组（82）紧邻穹顶（38）。 燃料喷射器（86,94）与两组（80,92,100）中的两个相关联，包括一组（80）和最靠近一组（80）的组（92）中的另一组。 组（80和92）和燃料喷射器（86,94）的空气喷射开口被构造，布置和定尺寸使得由每个组（80,92）喷射的空气的空气/燃料比不再多 大约5/1，剩余的一组空气喷射开口（100）被构造，布置和定尺寸，使得空气和燃料通过所有组（80,92,100）和燃料喷射器（ 86，94）是大致化学计量的。
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公开(公告)号：US5205117A
公开(公告)日：1993-04-27
申请号：US649601
申请日：1991-02-01
摘要： Difficulties in achieving reliable starts in gas turbine engines operating at high altitude are avoided in a gas turbine engine including a rotary compressor (10), a rotary turbine wheel (12) coupled to the compressor (10) to drive the same, and a nozzle (42) for directing gases of combustion against the turbine wheel (12). An annular combustor (34) has an outlet (40) connected to the nozzle (42) and an opposed dome (38) that is axially spaced from the outlet (40). At least three sets of air injection openings (80, 92, 100) are axially spaced from one another with one set (82) in close proximity to the dome (38). Fuel injectors (86, 94) are associated with two of the sets (80, 92, 100), including the one set (80) and another of the sets (92) that is nearest the one set (80). The air injection openings of the sets (80 and 92) and the fuel injectors (86, 94) are constructed, arranged and sized so that the air/fuel ratio of air injected by each of the sets (80, 92) is no more than about 5/1 and the remaining set of air injection openings (100) is constructed, arranged and sized so that the total air/fuel ratio of air and fuel through all of the sets (80, 92, 100) and fuel injectors (86, 94) is approximately stoichiometric.
摘要翻译： 在包括旋转式压缩机（10），联接到压缩机（10）的旋转涡轮机叶轮（12）以驱动旋转式压缩机（10）的燃气涡轮发动机中，避免了在高空作业的燃气涡轮发动机中实现可靠启动的困难，以及喷嘴 （42），用于将燃烧气体引导到涡轮机叶轮（12）。 环形燃烧器（34）具有连接到喷嘴（42）的出口（40）和与出口（40）轴向间隔开的相对的圆顶（38）。 至少三组空气喷射开口（80,92,100）彼此轴向间隔开，一组（82）紧邻穹顶（38）。 燃料喷射器（86,94）与两组（80,92,100）中的两个相关联，包括一组（80）和最靠近一组（80）的组（92）中的另一组。 组（80和92）和燃料喷射器（86,94）的空气喷射开口被构造，布置和定尺寸使得由每个组（80,92）喷射的空气的空气/燃料比不再多 大约5/1，剩余的一组空气喷射开口（100）被构造，布置和定尺寸，使得空气和燃料通过所有组（80,92,100）和燃料喷射器（ 86，94）是大致化学计量的。
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公开(公告)号：US5097657A
公开(公告)日：1992-03-24
申请号：US447448
申请日：1989-12-07
IPC分类号： F23R3/28
CPC分类号： F23R3/28
摘要： The problems of carbon build-up, poor fuel atomization, and fuel leakage in fuel injectors for turbine engines may be avoided if the fuel injector is fabricated by a method including the steps of: (a) providing a barrel (26) having an outlet end (44) adapted to be disposed in a turbine engine combustor (10), an inlet (46) adapted to be in fluid communication with the compressor of a turbine engine, an internal passage (40) extending between the inlet (46) and the outlet end (44) and a constriction (48) in the internal passage (40) between the inlet (46) and the outlet end (44) to define at least a partial venturi, (b) disposing a fuel tube (52) having a fuel injection end (54) within the internal passage (44), and (c) locating the fuel injector end (54) with respect to the constriction (48) at a position such that maximum fuel suction pressure is attained with a minimum reduction in air mass flow rate during operation of the injector.
摘要翻译： 如果燃料喷射器通过包括以下步骤的方法制造的方法可以避免用于涡轮发动机的燃料喷射器中碳积累，不良燃料雾化和燃料泄漏的问题：（a）提供具有出口 适于设置在涡轮发动机燃烧器（10）中的端部（44），适于与涡轮发动机的压缩机流体连通的入口（46），在所述入口（46）和 出口端（44）和入口（46）和出口端（44）之间的内部通道（40）中的收缩部（48），以限定至少部分文氏管，（b）设置燃料管（52） 在内部通道（44）内具有燃料喷射端（54），以及（c）将燃料喷射器端部（54）相对于收缩部（48）定位在使得最小燃料吸入压力达到最小的位置 降低注射器运行期间的空气质量流量。
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