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31. 发明申请

US20130167543A1 METHODS AND SYSTEMS FOR COOLING A TRANSITION NOZZLE 有权
标题翻译：用于冷却过渡喷嘴的方法和系统
公开(公告)号：US20130167543A1
公开(公告)日：2013-07-04
申请号：US13342475
申请日：2012-01-03
申请人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
发明人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
IPC分类号： F23R3/42 , B23P17/00
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/2322 , F23R3/002 , F23R3/005 , F23R3/04 , F23R3/34 , F23R2900/03043 , F23R2900/03341
摘要： A transition nozzle for use with a turbine assembly is provided. The transition nozzle includes a liner defining a combustion chamber therein, a wrapper circumscribing the liner such that a cooling duct is defined between the wrapper and the liner, a cooling fluid inlet configured to supply a cooling fluid to the cooling duct, and a plurality of ribs coupled between the liner and the wrapper such that a plurality of cooling channels are defined in the cooling duct.
摘要翻译：提供了一种与涡轮组件一起使用的过渡喷嘴。过渡喷嘴包括在其中限定燃烧室的衬套，围绕衬套的包装纸，使得在包装纸和衬垫之间限定冷却管道，构造成将冷却流体供应到冷却管道的冷却流体入口，以及多个连接在衬套和包装物之间的肋，使得在冷却管道中限定多个冷却通道。

32. 发明授权

US08387397B2 Flow conditioner for use in gas turbine component in which combustion occurs 失效
标题翻译：用于燃烧发生的燃气轮机部件的流量调节器
公开(公告)号：US08387397B2
公开(公告)日：2013-03-05
申请号：US12360490
申请日：2009-01-27
申请人： Wei Chen , Ronald James Chila , Eric William King
发明人： Wei Chen , Ronald James Chila , Eric William King
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/06 , F23R2900/03045
摘要： A gas turbine component in which combustion occurs. The gas turbine component includes a liner, including a first surface facing a first space and a second surface facing a second space, the liner being interposed between the first and second spaces and having a through-hole defined therein extending from the first to the second surface by which incoming flows proceed from the first space and to the second space. At least the first surface is formed to flow condition the incoming flows to resist separating from sidewalls of the through-hole.
摘要翻译：燃烧发生的燃气轮机部件。所述燃气涡轮机部件包括衬套，所述衬套包括面对第一空间的第一表面和面向第二空间的第二表面，所述衬垫插入在所述第一和第二空间之间，并且具有限定在其中的通孔，所述通孔从所述第一空间延伸到第二空间输入流从第一空间和第二空间进入的表面。至少第一表面形成为使进入的流动流动以抵抗与通孔的侧壁分离。

33. 发明授权

US08322976B2 High temperature seal for a turbine engine 有权
标题翻译：涡轮发动机的高温密封
公开(公告)号：US08322976B2
公开(公告)日：2012-12-04
申请号：US12098860
申请日：2008-04-07
申请人： Ronald James Chila , Kevin Weston McMahan , Timur Repikov
发明人： Ronald James Chila , Kevin Weston McMahan , Timur Repikov
IPC分类号： F04D29/04
CPC分类号： F01D9/023 , F01D11/005 , F02C7/28 , F05D2240/57 , F16J15/0887 , F16J15/104
摘要： A turbine includes a static member, a moveable member fluidly connected to the static member, and a flexible seal. The flexible seal includes a spring component having a base section mounted to one of the static member and the moveable member of the turbine and a plurality of biasing members. Each of the plurality of biasing members includes a first portion extending from the base section and a cantilevered portion. The flexible seal further includes a seal component provided on the cantilevered portion of each of the plurality of biasing members. The seal component is biased into contact with the other of the static member and the moveable member.
摘要翻译：涡轮机包括静态构件，流体连接到静止构件的可动构件和柔性密封件。柔性密封件包括弹簧部件，其具有安装到涡轮机的静止部件和可移动部件之一的基部以及多个偏置部件。多个偏置构件中的每一个包括从基部延伸的第一部分和悬臂部分。柔性密封件还包括设置在多个偏置构件中的每一个的悬臂部分上的密封部件。密封部件被偏置成与静止部件和可移动部件中的另一个接触。

34. 发明授权

US08307655B2 System for cooling turbine combustor transition piece 有权
标题翻译：涡轮机燃烧器过渡段冷却系统
公开(公告)号：US08307655B2
公开(公告)日：2012-11-13
申请号：US12784477
申请日：2010-05-20
申请人： Ronald James Chila , David William Cihlar
发明人： Ronald James Chila , David William Cihlar
IPC分类号： F02C1/00
CPC分类号： F23R3/002 , F01D9/023 , F02C7/12 , Y02T50/675
摘要： An air cooling hood offset from an exterior of the transition piece to define an air cooling passage between the air cooling hood and the exterior of the transition piece, wherein the air cooling hood comprises a plurality of air outlets disposed along the exterior of the transition piece, and the plurality of air outlets is configured to expel an airflow from the air cooling passage away from the exterior of the transition piece.
摘要翻译：空气冷却罩从过渡件的外部偏移以限定空气冷却罩和过渡件的外部之间的空气冷却通道，其中空气冷却罩包括沿着过渡件的外部设置的多个空气出口并且多个空气出口构造成从空气冷却通道排出远离过渡件外部的气流。

35. 发明申请

US20120234012A1 IMPINGEMENT SLEEVE AND METHODS FOR DESIGNING AND FORMING IMPINGEMENT SLEEVE 有权
标题翻译： IMPINGEMENT SLEEVE AND METHODS FOR DESIGN AND FORMING IMPINGEMENT SLEEVE
公开(公告)号：US20120234012A1
公开(公告)日：2012-09-20
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
发明人： Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar
IPC分类号： F23R3/42 , B23P17/00
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。

36. 发明授权

US08082739B2 Combustor exit temperature profile control via fuel staging and related method 有权
标题翻译：通过燃油分段控制燃烧器出口温度曲线及相关方法
公开(公告)号：US08082739B2
公开(公告)日：2011-12-27
申请号：US12758296
申请日：2010-04-12
申请人： Ronald James Chila , Mark Hadley
发明人： Ronald James Chila , Mark Hadley
IPC分类号： F02C7/22
CPC分类号： F23R3/346
摘要： A gas turbine combustor includes a combustion chamber defined by a combustor liner, the combustor liner having an upstream end cover supporting one or more nozzles arranged to supply fuel to the combustion chamber where the fuel mixes with air supplied from a compressor. A transition duct is connected between an aft end of the combustion chamber liner and a first stage turbine casing, the transition duct supplying gaseous products of combustion to the first stage turbine nozzle. One or more additional fuel injection nozzles are arranged at an aft end of the transition duct for introducing additional fuel into the transition duct upstream of the first stage turbine nozzle.
摘要翻译：燃气轮机燃烧器包括由燃烧器衬套限定的燃烧室，所述燃烧器衬套具有支撑一个或多个喷嘴的上游端盖，所述喷嘴布置成将燃料供应到燃烧室，在燃烧室中燃料与从压缩机供应的空气混合。过渡管道连接在燃烧室衬套的后端和第一级涡轮机壳体之间，该过渡管道向第一级涡轮喷嘴提供燃烧气体产物。一个或多个附加的燃料喷射喷嘴布置在过渡管道的后端，用于将额外的燃料引入到在第一级涡轮喷嘴上游的过渡管道中。

37. 发明申请

US20110247341A1 COMBUSTOR LINER HELICAL COOLING APPARATUS 有权
标题翻译： COMBUSTOR LINER HELIC冷却装置
公开(公告)号：US20110247341A1
公开(公告)日：2011-10-13
申请号：US12757610
申请日：2010-04-09
申请人： Kevin Weston McMahan , Ronald James Chila
发明人： Kevin Weston McMahan , Ronald James Chila
IPC分类号： F02C7/18
CPC分类号： F23M5/085 , F23R3/002 , F23R2900/03043 , F23R2900/03045
摘要： A combustor liner is provided. The combustor liner may include an upstream portion and a downstream end portion. The upstream portion may have a radius and a length along a generally longitudinal axis. The downstream end portion may have a radius and a length along the generally longitudinal axis. The downstream end portion may define a plurality of channels. Each of the plurality of channels may extend helically through the length of the downstream end portion. Each of the plurality of channels may be configured to flow an air flow therethrough, cooling the downstream end portion.
摘要翻译：提供燃烧器衬套。燃烧器衬套可以包括上游部分和下游端部分。上游部分可以具有沿着大致纵向轴线的半径和长度。下游端部可以具有沿着大致纵向轴线的半径和长度。下游端部可以限定多个通道。多个通道中的每一个可以螺旋地延伸穿过下游端部的长度。多个通道中的每一个可以被配置为使空气流通过其中，从而冷却下游端部。

38. 发明申请

US20090252593A1 COOLING APPARATUS FOR COMBUSTOR TRANSITION PIECE 有权
标题翻译：用于燃烧器过渡部件的冷却装置
公开(公告)号：US20090252593A1
公开(公告)日：2009-10-08
申请号：US12099352
申请日：2008-04-08
申请人： Ronald James Chila , David Purnell
发明人： Ronald James Chila , David Purnell
IPC分类号： F02C7/12 , F04D29/58
CPC分类号： F01D9/023 , F01D25/12 , F02C7/18 , F05D2230/21 , F05D2230/232 , Y02T50/675
摘要： Disclosed is an apparatus for cooling a transition piece of a combustor includes at least one wrapper disposed at the transition piece located outboard of the transition piece. At least one support boss is located between the at least one wrapper and the transition piece. The at least one support boss, the at least one wrapper, and transition piece define at least one cooling flow channel for directing flow for cooling the transition piece. A method of cooling a transition piece of a combustor includes flowing cooling flow into at least one cooling flow channel located at the transition piece, the at least one cooling flow channel defined by the transition piece, at least one wrapper located at the transition piece and located outboard of the transition piece, and at least one support boss located between the at least one wrapper and the transition piece. The cooling flow is directed via the at least one support boss and flows across an outer surface of the transition piece thereby cooling the transition piece.
摘要翻译：公开了一种用于冷却燃烧器的过渡件的设备，包括设置在过渡件外侧的过渡件上的至少一个包装纸。至少一个支撑凸台位于至少一个包装件和过渡件之间。至少一个支撑凸台，至少一个包装件和过渡件限定至少一个冷却流动通道，用于引导流动以冷却过渡件。一种冷却燃烧器的过渡件的方法包括将冷却流流入位于过渡件的至少一个冷却流动通道，由过渡件限定的至少一个冷却流动通道，位于过渡件处的至少一个包装物，位于过渡件的外侧，以及位于至少一个包装件和过渡件之间的至少一个支撑凸起。冷却流动经由至少一个支撑凸台引导并且流过过渡件的外表面，从而冷却过渡件。

39. 发明授权

US08966910B2 Methods and systems for cooling a transition nozzle 有权
标题翻译：用于冷却过渡喷嘴的方法和系统
公开(公告)号：US08966910B2
公开(公告)日：2015-03-03
申请号：US13164887
申请日：2011-06-21
申请人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
发明人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
IPC分类号： B21K25/00 , F02C1/00 , F01D9/02 , F23R3/00 , F23R3/06 , F23R3/34
CPC分类号： F01D9/023 , F05D2260/20 , F23R3/002 , F23R3/06 , F23R3/346 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y10T29/4932 , Y10T29/49323
摘要： A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion.
摘要翻译：涡轮组件包括构造成混合燃料和空气的燃料喷嘴和定向成从燃料喷嘴接收燃料和空气混合物的过渡喷嘴。过渡喷嘴包括过渡部分和与过渡部分一体形成的喷嘴部分。过渡喷嘴包括定向成引导空气以便于冷却过渡部分和/或喷嘴部分的多个开口。过渡部分被定向成将燃烧气体引向喷嘴部分。

40. 发明授权

US08826667B2 System and method for flow control in gas turbine engine 有权
标题翻译：燃气轮机发动机流量控制系统及方法
公开(公告)号：US08826667B2
公开(公告)日：2014-09-09
申请号：US13115018
申请日：2011-05-24
申请人： Patrick Benedict Melton , Bradley Donald Crawley , David William Cihlar , Robert Joseph Rohrssen , Ronald James Chila
发明人： Patrick Benedict Melton , Bradley Donald Crawley , David William Cihlar , Robert Joseph Rohrssen , Ronald James Chila
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/002 , F23R3/045 , F23R2900/03043 , Y02T50/675
摘要： A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure.
摘要翻译：一种系统包括燃气轮机燃烧器，其包括围绕燃烧区域设置的燃烧衬套，围绕燃烧衬套设置的流动套筒，在燃烧衬套和流动套筒之间的空气通道，以及在燃烧衬套和燃烧衬套之间延伸的结构流动套管该结构妨碍通过空气通道的气流路径。燃气轮机燃烧器还包括空气动力尾流减速器，其被配置成重新定向结构周围的气流以减少结构下游的尾流区域。

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