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公开(公告)号：US08950724B2
公开(公告)日：2015-02-10
申请号：US13535539
申请日：2012-06-28
IPC分类号： B64D27/00
CPC分类号： F01D25/28 , Y10T29/49231
摘要： A mounting system is provided to couple an engine unit including a turbine engine portion coupled to a gearbox portion about an axial axis to a support structure. An aft mounting device can couple the turbine engine portion to the support structure. A force determinator can be configured to determine a force load of the engine unit at the location of the aft mounting device. The length of the aft mounting device is adjustable between the turbine engine portion and the support structure in a radial direction to substantially align the gearbox portion and the engine portion relative to the axial axis. The aft mounting device may be sized to a desired length to correspond to a force load of the engine unit during the running condition.
摘要翻译： 提供了一种安装系统，以将包括联接到围绕轴向轴线的齿轮箱部分的涡轮发动机部分的发动机单元联接到支撑结构。 后部安装装置可以将涡轮发动机部分联接到支撑结构。 力确定器可以被配置成确定发动机单元在后部安装装置的位置处的力载荷。 后部安装装置的长度在涡轮发动机部分和支撑结构之间在径向上是可调节的，以使齿轮箱部分和发动机部分相对于轴向轴线基本上对准。 尾部安装装置的尺寸可以设定成所需长度以对应于在运行状态期间发动机单元的力载荷。
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公开(公告)号：US08943830B2
公开(公告)日：2015-02-03
申请号：US13397961
申请日：2012-02-16
IPC分类号： B32B3/26
CPC分类号： B32B3/26 , C23C10/48 , C23C16/12 , C23C16/56 , F23D14/16 , F23D2203/1012 , F23D2212/201 , Y10T428/249953
摘要： A porous metallic mat is provided. The porous metallic mat includes a plurality of fibers and a protective coating. The plurality of fibers is sintered into a mat configuration. The protective coating is provided on the porous metallic mat. The protective coating includes a diffusion aluminide configured to provide oxidation resistance to the porous metallic mat.
摘要翻译： 提供多孔金属垫。 多孔金属垫包括多根纤维和保护涂层。 多个纤维被烧结成垫子构型。 保护涂层设置在多孔金属垫上。 保护涂层包括被配置为对多孔金属垫提供抗氧化性的扩散铝化物。
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公开(公告)号：US08919132B2
公开(公告)日：2014-12-30
申请号：US13110179
申请日：2011-05-18
申请人： Gareth W. Oskam
发明人： Gareth W. Oskam
摘要： A method of operating a gas turbine engine includes directing a stream of liquid fuel to the combustor through a nozzle of a dual fuel injector. The method may also include directing a first quantity of compressed air to the stream of liquid fuel proximate the nozzle, and directing a second quantity of compressed air to the stream of liquid fuel downstream of the nozzle. The second quantity of compressed air may be larger than the first quantity of compressed air. The method may further include delivering the compressed air and the stream of liquid fuel to the combustor in a substantially unmixed manner.
摘要翻译： 操作燃气涡轮发动机的方法包括通过双燃料喷射器的喷嘴将液体燃料流引导到燃烧器。 该方法还可以包括将第一数量的压缩空气引导到靠近喷嘴的液体燃料流中，并且将第二数量的压缩空气引导到喷嘴下游的液体燃料流。 第二量的压缩空气可以大于第一量的压缩空气。 该方法还可以包括以大致不混合的方式将压缩空气和液体燃料流输送到燃烧器。
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公开(公告)号：US08672606B2
公开(公告)日：2014-03-18
申请号：US12654375
申请日：2009-12-17
申请人： Gabriel James Glynn , Charles Cornelius , Ian Trevor Brown , Daniel James Doll , Jason Michael Robertson
发明人： Gabriel James Glynn , Charles Cornelius , Ian Trevor Brown , Daniel James Doll , Jason Michael Robertson
IPC分类号： F01D25/28
CPC分类号： F01D25/28 , F01D25/285 , F02C7/20 , F05D2230/60 , F05D2230/68 , F05D2230/70 , F05D2250/313 , F16M1/04 , F16M5/00 , Y10T29/49318 , Y10T29/49721 , Y10T29/4973 , Y10T29/49895 , Y10T29/49998 , Y10T29/53548 , Y10T29/53961
摘要： A gas turbine engine includes a compressor having first annular connection structure at a forward end portion of an air inlet housing of the compressor. The gas turbine engine may also include intake ducting having second annular connection structure adjacent a central passage of the intake ducting. The first annular connection structure and the second annular connection structure may form at least part of an interface between the air inlet housing and the intake ducting during operation of the gas turbine engine. The first and second annular connection structures may have shapes allowing the first annular connection structure to be moved through and beyond the second annular connection structure in a forward direction, the forward direction being opposite a direction of compressed air flow in the compressor during operation.
摘要翻译： 燃气涡轮发动机包括在压缩机的空气入口壳体的前端部处具有第一环形连接结构的压缩机。 燃气涡轮发动机还可以包括具有邻近进气管道的中心通道的第二环形连接结构的进气管道。 第一环形连接结构和第二环形连接结构可以在燃气涡轮发动机的操作期间形成空气入口壳体和进气管道之间的界面的至少一部分。 第一和第二环形连接结构可以具有允许第一环形连接结构在正向方向上移动通过第二环形连接结构并且超过第二环形连接结构的形状，正向在操作期间与压缩机中的压缩空气流的方向相反。
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公开(公告)号：US08590151B2
公开(公告)日：2013-11-26
申请号：US12654374
申请日：2009-12-17
IPC分类号： F01D25/28
CPC分类号： F16M5/00 , F01D25/285 , F05D2230/60 , F05D2230/68 , F05D2230/70 , F05D2250/313 , F16M1/04
摘要： A power system includes a gas turbine engine, which may include a gear box. The gear box may include a pipe connection configured to receive a removable pipe. The power system may also include a moveable support configured to fasten to the pipe connection to at least partially support the gear box.
摘要翻译： 电力系统包括燃气涡轮发动机，其可以包括齿轮箱。 齿轮箱可以包括被配置为接收可移除管道的管道连接。 动力系统还可以包括可移动支撑件，其构造成紧固到管道连接件以至少部分地支撑齿轮箱。
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公开(公告)号：US20130202192A1
公开(公告)日：2013-08-08
申请号：US13365488
申请日：2012-02-03
CPC分类号： G06T7/0004 , F01D5/00 , F02C1/00 , G06T2207/30164
摘要： A method of measuring creep strain in a gas turbine engine component, where at least a portion of the component has a material disposed thereon, and where the material has a plurality of markings providing a visually distinct pattern. The method may include capturing an image of at least a portion of the markings after an operational period of the gas turbine engine, and determining creep strain information of the component. The creep strain information may be determined by correlating the image captured after the operational period to an image captured before the operational period.
摘要翻译： 一种测量燃气涡轮发动机部件中的蠕变应变的方法，其中所述部件的至少一部分具有设置在其上的材料，并且其中所述材料具有提供视觉上不同图案的多个标记。 该方法可以包括在燃气涡轮发动机的操作周期之后捕获至少一部分标记的图像，以及确定部件的蠕变应变信息。 蠕变应变信息可以通过将在操作周期之后捕获的图像与在操作周期之前捕获的图像相关联来确定。
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公开(公告)号：US20130192237A1
公开(公告)日：2013-08-01
申请号：US13362189
申请日：2012-01-31
申请人： Gareth W. Oskam
发明人： Gareth W. Oskam
CPC分类号： F02C7/22 , F23C2205/10 , F23D2900/14482 , F23R3/286
摘要： A fuel injector system for a turbine engine may include a center body disposed about a longitudinal axis and a barrel housing positioned radially outwardly from the center body to define an annular passageway therebetween. The fuel injector may also include one or more fuel discharge outlets positioned in the annular passageway. The one or more fuel discharge outlets may be configured to discharge pulses of a fuel into the annular passageway. The fuel injector may further include one or more fluidic oscillators fluidly coupled to the one or more fuel discharge outlets. The one or more fluidic oscillators may be configured to induce pulsations in the fuel discharged by the one or more fuel discharge outlets.
摘要翻译： 用于涡轮发动机的燃料喷射器系统可以包括围绕纵向轴线设置的中心体和从中心体径向向外定位的筒体，以在其间限定环形通道。 燃料喷射器还可以包括位于环形通道中的一个或多个燃料排出口。 一个或多个燃料排出口可以被配置为将燃料的脉冲排放到环形通道中。 燃料喷射器还可以包括流体耦合到一个或多个燃料排放出口的一个或多个流体振荡器。 一个或多个流体振荡器可以被配置为引起由一个或多个燃料排放出口排出的燃料中的脉动。
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公开(公告)号：US20130152593A1
公开(公告)日：2013-06-20
申请号：US13326798
申请日：2011-12-15
申请人： Gareth W. Oskam
发明人： Gareth W. Oskam
CPC分类号： F23R3/28 , F02C3/30 , F23D11/107 , F23D14/22 , F23R3/36
摘要： A fuel injector for a gas turbine engine may include an injector housing having a central cavity configured to be fluidly coupled to a combustor of the turbine engine. The central cavity may also be configured to direct a first fuel into the combustor substantially unmixed with air. The fuel injector may also include an annular air discharge outlet circumferentially disposed about the downstream end of the central cavity. The air discharge outlet may be configured to discharge compressed air into the combustor circumferentially about the first fuel from the central cavity. The fuel injector may also include an annular fuel discharge outlet circumferentially disposed about the air discharge outlet at the downstream end. The fuel discharge outlet may be configured to discharge a second fuel into the combustor circumferentially about the compressed air from the air discharge outlet.
摘要翻译： 用于燃气涡轮发动机的燃料喷射器可以包括具有被配置为流体地联接到涡轮发动机的燃烧器的中心腔的喷射器壳体。 中心腔也可以构造成将第一燃料引导到与空气基本上不混合的燃烧器中。 燃料喷射器还可以包括围绕中心腔的下游端周向设置的环形空气排出口。 空气排放出口可以构造成将压缩空气从中心腔排出到围绕第一燃料的周向周围。 燃料喷射器还可以包括围绕下游端的排气出口周向设置的环形燃料排出口。 燃料排出口可以被配置为将第二燃料从空气排出口排出到围绕压缩空气的周向周围的燃烧器中。
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公开(公告)号：US08381531B2
公开(公告)日：2013-02-26
申请号：US12289969
申请日：2008-11-07
IPC分类号： F02C1/00
摘要： A fuel injector for a gas turbine engine may include a pilot assembly extending along a longitudinal axis. The pilot assembly may be configured to direct a pilot fuel-air mixture to a combustor of the gas turbine engine. The fuel injector may also include a rich catalyst module circumferentially disposed about the pilot assembly. The catalyst module may be configured to simultaneously direct a stream of compressed air and a stream of first fuel-air mixture therethrough without intermixing. The fuel injector may also include a post mix zone disposed downstream of the catalyst module. The post mix zone may be configured to mix the compressed air and the first fuel air mixture to create a main fuel-air mixture. The fuel injector may further include an air swirler disposed downstream of the post mix zone. The air swirler may be configured to direct the main fuel-air mixture to the combustor without intermixing with the pilot fuel-air mixture.
摘要翻译： 用于燃气涡轮发动机的燃料喷射器可以包括沿纵向轴线延伸的导向组件。 导向组件可以被配置成将先导燃料 - 空气混合物引导到燃气涡轮发动机的燃烧器。 燃料喷射器还可以包括围绕导向组件周向设置的富催化剂模块。 催化剂模块可以被配置成同时引导压缩空气流和第一燃料 - 空气混合物流而不混合。 燃料喷射器还可以包括设置在催化剂模块下游的后混合区域。 后混合区可以被配置为混合压缩空气和第一燃料空气混合物以产生主要的燃料 - 空气混合物。 燃料喷射器还可以包括设置在后混合区域下游的空气旋流器。 空气旋流器可以被配置成将主燃料 - 空气混合物引导到燃烧器，而不与先导燃料 - 空气混合物混合。
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公开(公告)号：US20120324900A1
公开(公告)日：2012-12-27
申请号：US13166981
申请日：2011-06-23
CPC分类号： F23R3/14 , F23C2900/07001 , F23D2900/14021 , F23R3/16 , F23R3/286 , F23R2900/00014
摘要： A fuel injector for a turbine engine may include a body member disposed about a longitudinal axis, and a barrel member located radially outwardly from the body member. The fuel injector may also include an annular passageway extending between the body member and the barrel member from a first end to a second end. The first end may be configured to be fluidly coupled to a compressor of the turbine engine and the second end may be configured to be fluidly coupled to a combustor of the turbine engine. The fuel injector may also include a perforated plate positioned proximate the first end of the passageway. The perforated plate may be configured to direct compressed air into the annular passageway with a first pressure drop. The fuel injector may also include at least one fuel discharge orifice positioned downstream of the perforated plate. The at least one fuel discharge orifice may be configured to discharge a fuel into the annular passageway with a second pressure drop. The second pressure drop may have a value between about the first pressure drop and about 1.75 times the first pressure drop.
摘要翻译： 用于涡轮发动机的燃料喷射器可以包括围绕纵向轴线设置的主体部件和从主体部件径向向外定位的筒部件。 燃料喷射器还可以包括从第一端到第二端在主体构件和筒构件之间延伸的环形通道。 第一端可以被配置为流体地联接到涡轮发动机的压缩机，并且第二端可被配置为流体地联接到涡轮发动机的燃烧器。 燃料喷射器还可以包括邻近通道的第一端定位的多孔板。 多孔板可以构造成以第一压降将压缩空气引导到环形通道中。 燃料喷射器还可以包括位于多孔板下游的至少一个燃料排放孔。 至少一个燃料排放孔可以构造成以第二压降将燃料排放到环形通道中。 第二压降可以具有在大约第一压力下降与第一压力下降约1.75倍之间的值。
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