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111. 发明申请

US20100077761A1 IMPINGEMENT COOLED COMBUSTOR SEAL 有权
标题翻译：冲击冷却COMBUSTOR密封
公开(公告)号：US20100077761A1
公开(公告)日：2010-04-01
申请号：US12242013
申请日：2008-09-30
申请人： Thomas Edward Johnson , Patrick Benedict Melton
发明人： Thomas Edward Johnson , Patrick Benedict Melton
IPC分类号： F02C7/12 , F02C7/28
CPC分类号： F23R3/44 , F23R2900/00012 , F23R2900/03044 , Y02T50/675
摘要： Disclosed is a combustor seal including a seal support locatable at a first combustor component and having a plurality of through impingement holes. A wave-shaped seal located at the seal support and defining at least one seal cavity between the wave-shaped seal and the seal support. A peak of the wave-shaped seal is locatable at a second combustor component. The wave-shaped seal includes at least one through passageway located upstream of the peak capable of flowing cooling fluid therethrough into the at least one seal cavity and through the plurality of impingement holes thereby cooling the first combustor component. Further disclosed is a combustor including a combustor seal and a method for cooling a first combustor component.
摘要翻译：公开了一种燃烧器密封件，其包括可定位在第一燃烧器部件处并具有多个通过冲击孔的密封支撑件。位于密封支撑件处的波形密封件并且在波形密封件和密封件支撑件之间限定至少一个密封腔。波形密封件的峰值位于第二燃烧器部件处。波形密封件包括位于峰顶部的至少一个贯通通道，其能够将冷却流体从其中流动通过其中进入至少一个密封空腔中，并且穿过多个冲击孔从而冷却第一燃烧器部件。还公开了一种包括燃烧器密封件和用于冷却第一燃烧器部件的方法的燃烧器。

112. 发明授权

US09267690B2 Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same 有权
标题翻译：涡轮机燃烧器喷嘴包括单片喷嘴部件及其形成方法
公开(公告)号：US09267690B2
公开(公告)日：2016-02-23
申请号：US13482540
申请日：2012-05-29
申请人： Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
发明人： Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
IPC分类号： F23R3/28 , F23R3/32
CPC分类号： F23R3/283 , F23R3/286 , F23R2900/00017 , F23R2900/00018 , Y10T29/49323
摘要： A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements.
摘要翻译：涡轮机燃烧器喷嘴包括具有板元件和多个喷嘴元件的单片喷嘴部件。多个喷嘴元件中的每一个包括从板元件延伸到第二端的第一端。板元件和多个喷嘴元件形成为整体部件。板构件与喷嘴部件接合。板构件包括限定第一和第二表面的外边缘和在第一和第二表面之间延伸的多个开口。多个开口被配置和设置成与多个喷嘴元件中对应的喷嘴元件的对应的第二端对准并接收。

113. 发明授权

US09151500B2 System for supplying a fuel and a working fluid through a liner to a combustion chamber 有权
标题翻译：用于将燃料和工作流体通过衬套供应到燃烧室的系统
公开(公告)号：US09151500B2
公开(公告)日：2015-10-06
申请号：US13420715
申请日：2012-03-15
申请人： Wei Chen , Patrick Benedict Melton , Russell DeForest , Lucas John Stoia , Richard Martin DiCintio
发明人： Wei Chen , Patrick Benedict Melton , Russell DeForest , Lucas John Stoia , Richard Martin DiCintio
IPC分类号： F23R3/34 , F23R3/04 , F23R3/28 , F01D9/02
CPC分类号： F23R3/04 , F01D9/023 , F23R3/286 , F23R3/346
摘要： A system for supplying a working fluid to a combustor includes a combustion chamber and a flow sleeve that circumferentially surrounds at least a portion of the combustion chamber. A tube provides fluid communication for the working fluid to flow through the flow sleeve and into the combustion chamber, wherein the tube comprises an axial centerline. A first set of injectors are circumferentially arranged around the tube and angled radially with respect to the axial centerline of the tube, wherein the first set of injectors provide fluid communication for the working fluid to flow through a wall of the tube.
摘要翻译：用于向燃烧器供应工作流体的系统包括燃烧室和周向围绕燃烧室的至少一部分的流动套管。管提供流体连通以使工作流体流过流动套筒并进入燃烧室，其中管包括轴向中心线。第一组喷射器围绕管周向布置并且相对于管的轴向中心线径向成角度，其中第一组喷射器为工作流体提供流体连通以流过管的壁。

114. 发明授权

US09046038B2 Combustor 有权
标题翻译：燃烧器
公开(公告)号：US09046038B2
公开(公告)日：2015-06-02
申请号：US13600769
申请日：2012-08-31
申请人： Lucas John Stoia , Patrick Benedict Melton
发明人： Lucas John Stoia , Patrick Benedict Melton
IPC分类号： F01D25/28 , F02C7/20 , F02C3/14 , F23R3/10 , F23R3/28
CPC分类号： F02C7/20 , F01D25/28 , F02C3/14 , F23R3/10 , F23R3/283
摘要： A combustor includes a breech end, a plurality of fuel nozzles connected to the breech end and extending downstream from the breech end, and a shroud that circumferentially surrounds the plurality of fuel nozzles inside the combustor. A support extends radially inside at least a portion of the shroud. A leaf spring is between the support and one or more of the plurality of fuel nozzles, wherein each leaf spring includes at least three leaves.
摘要翻译：燃烧器包括后膛端，连接到后膛端并从后膛末端延伸的多个燃料喷嘴，以及围绕燃烧器内部的多个燃料喷嘴的护罩。支撑件在护罩的至少一部分内径向延伸。支撑件和多个燃料喷嘴中的一个或多个之间的板簧在其中，每个板簧包括至少三个叶片。

115. 发明授权

US09010082B2 Turbine engine and method for flowing air in a turbine engine 有权
标题翻译：涡轮发动机和在涡轮发动机中流动空气的方法
公开(公告)号：US09010082B2
公开(公告)日：2015-04-21
申请号：US13342587
申请日：2012-01-03
申请人： Lucas John Stoia , Patrick Benedict Melton , Predrag Peja Popovic
发明人： Lucas John Stoia , Patrick Benedict Melton , Predrag Peja Popovic
IPC分类号： F23R3/26 , F23R3/04
CPC分类号： F23R3/045 , F23R3/26
摘要： According to one aspect of the invention, a gas turbine engine includes a combustor, a fuel nozzle placed in an end of the combustor, and a passage configured to receive an air flow from a compressor discharge casing, wherein the passage directs the air flow into a chamber downstream of the nozzle, wherein a chamber pressure is lower than a compressor discharge casing pressure. The gas turbine engine also includes a flow control device configured to control the air flow from the compressor discharge casing into the passage.
摘要翻译：根据本发明的一个方面，一种燃气涡轮发动机包括燃烧器，设置在燃烧器的端部的燃料喷嘴，以及构造成接收来自压缩机排出壳体的空气流的通道，其中通道将气流引导到在喷嘴下游的腔室，其中室压力低于压缩机排气套管压力。燃气涡轮发动机还包括流量控制装置，该流量控制装置被配置为控制从压缩机排放壳体进入通道的空气流。

116. 发明授权

US08997501B2 System for mounting combustor transition piece to frame of gas turbine engine 有权
标题翻译：将燃烧器过渡件安装在燃气轮机发动机机架上的系统
公开(公告)号：US08997501B2
公开(公告)日：2015-04-07
申请号：US13152117
申请日：2011-06-02
申请人： David William Cihlar , Patrick Benedict Melton , John Drake Vanselow
发明人： David William Cihlar , Patrick Benedict Melton , John Drake Vanselow
IPC分类号： F02C7/20 , F02C1/00 , F01D9/02
CPC分类号： F01D9/023 , F05D2250/411 , F05D2260/30
摘要： A system includes a combustor transition piece configured to mount between a combustor and a turbine of a gas turbine engine. The combustor transition piece includes a hollow body with an internal flow passage extending from an upstream end portion to a downstream end portion. The combustor transition piece also includes an aft frame coupled to the downstream end portion of the hollow body, an aft flange coupled to the aft frame, and a mounting lug removably coupled to the aft frame at a first joint. The mounting lug is configured to removably couple to a mounting bracket at a second joint.
摘要翻译：一种系统包括构造成安装在燃气轮机和燃气轮机的涡轮机之间的燃烧器过渡件。燃烧器过渡件包括具有从上游端部向下游端部延伸的内部流路的中空体。燃烧器过渡件还包括联接到中空本体的下游端部的后框架，联接到后框架的后凸缘和在第一接头处可拆卸地联接到后框架的安装凸耳。安装凸耳构造成在第二关节处可拆卸地联接到安装支架。

117. 发明授权

US08894407B2 Combustor and method for supplying fuel to a combustor 有权
标题翻译：用于向燃烧器供应燃料的燃烧器和方法
公开(公告)号：US08894407B2
公开(公告)日：2014-11-25
申请号：US13294247
申请日：2011-11-11
申请人： Lucas John Stoia , Patrick Benedict Melton
发明人： Lucas John Stoia , Patrick Benedict Melton
IPC分类号： F23N1/00 , F23R3/28
CPC分类号： F23R3/286 , F23R3/283
摘要： A combustor includes an end cap, a combustion chamber downstream from the end cap, and a plurality of tubes that extends through the end cap to provide fluid communication through the end cap to the combustion chamber. A casing surrounds the end cap, and a conduit extends from the casing to the end cap. A duct extends around the conduit and inside the end cap to provide fluid communication to the end cap. A method for supplying fuel to a combustor includes flowing a working fluid through a plurality of tubes that extends axially through an end cap, supplying a first fluid through a conduit into the end cap, and supplying a second fluid through a duct spiraling around the conduit into the end cap.
摘要翻译：燃烧器包括端盖，在端盖下游的燃烧室，以及延伸穿过端盖的多个管，以提供通过端盖到燃烧室的流体连通。壳体围绕端盖，并且导管从壳体延伸到端盖。导管围绕导管延伸并且在端盖内部提供与端盖的流体连通。用于向燃烧器供应燃料的方法包括使工作流体流过穿过端盖的轴向延伸的多个管，将第一流体通过导管提供到端盖中，并且通过围绕导管螺旋地供应第二流体进入端盖。

118. 发明授权

US08887508B2 Impingement sleeve and methods for designing and forming impingement sleeve 有权
标题翻译：冲击套筒和冲击套管的设计和成型方法
公开(公告)号：US08887508B2
公开(公告)日：2014-11-18
申请号：US13048394
申请日：2011-03-15
申请人： Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Matthew Paul Berkebile , Wei Chen , John Drake Vanselow
发明人： Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Matthew Paul Berkebile , Wei Chen , John Drake Vanselow
IPC分类号： F23R3/06 , F01D9/02
CPC分类号： F01D9/023 , F05D2260/201 , F23R2900/03044 , Y10T29/49229
摘要： An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, a method for designing an impingement sleeve is disclosed. The method includes determining a desired operational value for a transition piece, inputting a combustor characteristic into a processor, and utilizing the combustor characteristic in the processor to determine a cooling hole pattern for the impingement sleeve, the cooling hole pattern comprising a plurality of cooling holes, at least a portion of the plurality of cooling holes being generally longitudinally asymmetric, the cooling hole pattern providing the desired operational value.
摘要翻译：公开了一种冲击套筒和用于设计和形成冲击套筒的方法。在一个实施例中，公开了一种用于设计冲击套筒的方法。该方法包括确定过渡件的期望操作值，将燃烧器特性输入到处理器中，以及利用处理器中的燃烧器特性来确定冲击套筒的冷却孔图案，冷却孔图案包括多个冷却孔所述多个冷却孔的至少一部分大致纵向不对称，所述冷却孔图案提供期望的操作值。

119. 发明申请

US20140014792A1 FASTENER ASSEMBLY FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮的紧固件总成
公开(公告)号：US20140014792A1
公开(公告)日：2014-01-16
申请号：US13548263
申请日：2012-07-13
申请人： Christopher Paul Willis , Patrick Benedict Melton , Lucas John Stoia , Richard Martin DiCintio , David William Cihlar
发明人： Christopher Paul Willis , Patrick Benedict Melton , Lucas John Stoia , Richard Martin DiCintio , David William Cihlar
IPC分类号： F16B21/00 , F16M13/02
CPC分类号： F16B41/002 , F16B43/005
摘要： A fastener assembly configured for use within an opening defined in a transition piece bracket is disclosed. The fastener assembly may generally include a fastener having a head configured to be positioned proximal to a first end of the opening and a body. The body may include a shank portion, a threaded portion opposite the shank portion and a recessed portion defined between the shank portion and the threaded portion. The fastener assembly may also include a retention member configured to be positioned within the opening adjacent the recessed portion such that the retention member engages at least one of the shank portion or the threaded portion as the fastener is moved within the opening. In addition, the fastener assembly may include a biasing member engaged against the retention member. The biasing member may be configured to bias the head of the fastener away from the first end of the opening.
摘要翻译：公开了一种构造用于在过渡件支架中限定的开口内使用的紧固件组件。紧固件组件通常可以包括紧固件，该紧固件具有被配置成邻近开口的第一端定位的头部和主体。主体可以包括柄部分，与柄部分相对的螺纹部分和限定在柄部分和螺纹部分之间的凹部。紧固件组件还可以包括保持构件，该保持构件构造成邻近凹部部分定位在开口内，使得当紧固件在开口内移动时，保持构件接合柄部分或螺纹部分中的至少一个。另外，紧固件组件可以包括抵靠保持构件接合的偏置构件。偏置构件可以构造成将紧固件的头部偏离开口的第一端。

120. 发明申请

US20140000267A1 TRANSITION DUCT FOR A GAS TURBINE 审中-公开
标题翻译：用于气体涡轮的过渡式导管
公开(公告)号：US20140000267A1
公开(公告)日：2014-01-02
申请号：US13538333
申请日：2012-06-29
申请人： Patrick Benedict Melton
发明人： Patrick Benedict Melton
IPC分类号： F02C7/00
CPC分类号： F01D9/023
摘要： A transition duct for a combustor of a gas turbine generally includes an end frame that has a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion between the radially outer and inner portions. A slot may be in at least one of the radially outer portion, radially inner portion, first side portion, or second side portion of the end frame. A first plurality of axially extending passages may pass through the end frame and intersect with the slot. A terminal end of the end frame may be uninterrupted adjacent to the slot.
摘要翻译：用于燃气轮机的燃烧器的过渡管通常包括具有径向外部的端部框架，与径向外部相对的径向内部，在径向外部和内部之间的第一侧部，以及第二侧部与径向外部和内部之间的第一侧部相对。狭槽可以在端框架的径向外部部分，径向内部部分，第一侧部分或第二侧部分中的至少一个中。第一多个轴向延伸的通道可以穿过端框架并与槽相交。端框的终端可以不间断地邻近该槽。

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