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1.发明公开Integrated fuel nozzle with feedback control for a gas turbine engine 有权IntegrierteBrennstoffdüsemit Feedbacksteuerungfürein Gasturbinentriebwerk
公开(公告)号：EP2014989A2
公开(公告)日：2009-01-14
申请号：EP08251631.1
申请日：2008-05-07
CPC分类号： F23R3/286 , F23N1/005 , F23N5/003 , F23N5/082 , F23N2041/20 , Y02T50/677
摘要： A gas turbine engine (10) includes a combustor (16) having a fuel nozzle assembly (24) for delivering fuel to a combustion chamber (20). A sensor (40) is at least partially housed within the fuel nozzle assembly (24) for sensing a parameter associated with the delivery of fuel to the combustion chamber (28). In one example, the sensor (40) is an optical sensor coupled to an optical decoder (42) for ascertaining the parameter. A trim valve (34) is in communication with the fuel nozzle assembly. A controller (44) is in communication with the sensor (40) and is programmed to actuate the trim valve (34) to adjust the amount of fuel delivered through the fuel nozzle assembly in response to the parameter. In one example, an end of the optical sensor (40) is arranged near a fuel exit (38) of the fuel nozzle assembly. The controller (44) actuates the trim valve (34) for the fuel nozzle assembly to achieve a desired air/fuel ratio and/or balance the fuel delivery of the fuel nozzle assembly relative to another fuel nozzle assembly within the gas turbine engine's combustor system.
摘要翻译： 燃气涡轮发动机（10）包括具有用于将燃料输送到燃烧室（20）的燃料喷嘴组件（24）的燃烧器（16）。 传感器（40）至少部分地容纳在燃料喷嘴组件（24）内，用于感测与将燃料输送到燃烧室（28）相关联的参数。 在一个示例中，传感器（40）是耦合到光学解码器（42）以确定参数的光学传感器。 调节阀（34）与燃料喷嘴组件连通。 控制器（44）与传感器（40）连通，并且被编程为致动调节阀（34）以响应于参数来调节通过燃料喷嘴组件输送的燃料量。 在一个示例中，光学传感器（40）的端部布置在燃料喷嘴组件的燃料出口（38）附近。 控制器（44）致动用于燃料喷嘴组件的调节阀（34）以实现期望的空气/燃料比和/或平衡燃料喷嘴组件相对于燃气涡轮发动机的燃烧器系统内的另一个燃料喷嘴组件的燃料输送 。
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公开(公告)号：EP1801502A3
公开(公告)日：2010-07-07
申请号：EP06255405.0
申请日：2006-10-20
CPC分类号： F23R3/002 , F23R3/007 , F23R2900/00017 , F23R2900/03044
摘要： A combustor liner assembly (10) includes an outer shell (14) made of a ceramic composite and an inner heat shell (16) that is supported within the outer shell (14). The inner heat shield (16) defines a surface that is exposed to combustion gases. The inner heat shield (16) is made of material that is compatible with the ceramic matrix composite and that provides favorable thermal gradient capability for a combustion chamber.
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公开(公告)号：EP1522792B1
公开(公告)日：2013-01-02
申请号：EP04256235.5
申请日：2004-10-08
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4.发明公开
公开(公告)号：EP2014989A3
公开(公告)日：2012-06-06
申请号：EP08251631.1
申请日：2008-05-07
CPC分类号： F23R3/286 , F23N1/005 , F23N5/003 , F23N5/082 , F23N2041/20 , Y02T50/677
摘要： A gas turbine engine (10) includes a combustor (16) having a fuel nozzle assembly (24) for delivering fuel to a combustion chamber (20). A sensor (40) is at least partially housed within the fuel nozzle assembly (24) for sensing a parameter associated with the delivery of fuel to the combustion chamber (28). In one example, the sensor (40) is an optical sensor coupled to an optical decoder (42) for ascertaining the parameter. A trim valve (34) is in communication with the fuel nozzle assembly. A controller (44) is in communication with the sensor (40) and is programmed to actuate the trim valve (34) to adjust the amount of fuel delivered through the fuel nozzle assembly in response to the parameter. In one example, an end of the optical sensor (40) is arranged near a fuel exit (38) of the fuel nozzle assembly. The controller (44) actuates the trim valve (34) for the fuel nozzle assembly to achieve a desired air/fuel ratio and/or balance the fuel delivery of the fuel nozzle assembly relative to another fuel nozzle assembly within the gas turbine engine's combustor system.
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公开(公告)号：EP2905427B1
公开(公告)日：2018-12-05
申请号：EP15153210.8
申请日：2015-01-30
发明人： Porter, Steven D. , Ols, John T.
CPC分类号： F01D11/005 , F01D9/02 , F01D9/041 , F01D9/06 , F01D25/26 , F02C3/04 , F02C7/28 , F05D2220/32 , F05D2240/128 , F05D2240/58 , F05D2240/80
摘要： A sealing arrangement (99) for a gas turbine engine (20) according to an exemplary aspect of the present disclosure includes, among other things, a groove (82) that extends between an upstream rail (84) and a downstream rail (86), a complementary static structure (65) spaced from the groove (82), and a seal (90) positioned within the groove (82) and configured to seal a clearance between at least one of the upstream rail (84) and the downstream rail (86) and the complementary static structure (65).
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6.发明授权
公开(公告)号：EP2014989B1
公开(公告)日：2016-07-27
申请号：EP08251631.1
申请日：2008-05-07
CPC分类号： F23R3/286 , F23N1/005 , F23N5/003 , F23N5/082 , F23N2041/20 , Y02T50/677
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公开(公告)号：EP2905427A1
公开(公告)日：2015-08-12
申请号：EP15153210.8
申请日：2015-01-30
发明人： Porter, Steven D. , Ols, John T.
CPC分类号： F01D11/005 , F01D9/02 , F01D9/041 , F01D9/06 , F01D25/26 , F02C3/04 , F02C7/28 , F05D2220/32 , F05D2240/128 , F05D2240/58 , F05D2240/80
摘要： A sealing arrangement (99) for a gas turbine engine (20) according to an exemplary aspect of the present disclosure includes, among other things, a groove (82) that extends between an upstream rail (84) and a downstream rail (86), a complementary static structure (65) spaced from the groove (82), and a seal (90) positioned within the groove (82) and configured to seal a clearance between at least one of the upstream rail (84) and the downstream rail (86) and the complementary static structure (65).
摘要翻译： 根据本公开的示例性方面的用于燃气涡轮发动机（20）的密封装置（99）包括在上游轨道（84）和下游轨道（86）之间延伸的凹槽（82） ，与凹槽（82）间隔开的互补的静态结构（65）和位于所述凹槽（82）内的密封件（90），并被构造成密封所述上游导轨（84）和所述下游导轨（84）中的至少一个之间的间隙 （86）和互补静态结构（65）。
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公开(公告)号：EP1801502B1
公开(公告)日：2014-12-03
申请号：EP06255405.0
申请日：2006-10-20
CPC分类号： F23R3/002 , F23R3/007 , F23R2900/00017 , F23R2900/03044
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公开(公告)号：EP1801502A2
公开(公告)日：2007-06-27
申请号：EP06255405.0
申请日：2006-10-20
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F23R3/007 , F23R2900/00017 , F23R2900/03044
摘要： A combustor liner assembly (10) includes an outer shell (14) made of a ceramic composite and an inner heat shell (16) that is supported within the outer shell (14). The inner heat shield (16) defines a surface that is exposed to combustion gases. The inner heat shield (16) is made of material that is compatible with the ceramic matrix composite and that provides favorable thermal gradient capability for a combustion chamber.
摘要翻译： 燃烧器衬套组件（10）包括由陶瓷复合材料制成的外壳（14）和支撑在外壳（14）内的内热壳体（16）。 内部隔热罩（16）限定了暴露于燃烧气体的表面。 内部隔热罩（16）由与陶瓷基体复合材料相容的材料制成，为燃烧室提供有利的热梯度能力。
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公开(公告)号：EP1522792A1
公开(公告)日：2005-04-13
申请号：EP04256235.5
申请日：2004-10-08
摘要： A gas turbine engine combustor (20) has inboard and outboard walls (32,134). A forward bulkhead (36) extends between the walls and cooperates therewith to define a combustor interior volume. In longitudinal section, a first portion (54) of the combustor interior volume converges from fore to aft and a second portion (56), aft of the first portion (54) converges from fore to aft more gradually than the first portion (54).
摘要翻译： 燃气涡轮发动机燃烧器（20）具有内侧和外侧壁（32,134）。 前隔板（36）在壁之间延伸并与其配合以限定燃烧室内部容积。 在纵向截面中，燃烧器内部体积的第一部分（54）从前部向后收缩，并且第一部分（54）的后部的第二部分（56）比第一部分（54）更加逐渐地从前部向后方会聚， 。
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