公开(公告)号：US20130036742A1

公开(公告)日：2013-02-14

申请号：US13652275

申请日：2012-10-15

申请人： GENERAL ELECTRIC COMPANY

发明人： Ronald James Chila

IPC分类号： F23R3/26 ,  F02C7/00

CPC分类号： F23R3/06 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

摘要： A turbine engine with a combustor that includes a hollow wall about a combustor liner. The combustor liner includes an inner surface facing inwardly toward a combustion chamber. The turbine engine includes a first air flow path in an upstream direction through the hollow wall toward a head end of the combustor. The first air flow path includes a plurality of bypass openings extending through the combustor liner to the inner surface to supply a first cooling film to a downstream end portion of the combustor liner. The turbine engine further includes a second flow path in a second direction opposite the upstream direction through the hollow wall. The second flow path includes a plurality of film holes extending through the combustor liner to the inner surface to supply a second cooling film to the downstream end portion of the combustor liner downstream of the first cooling film.

摘要翻译： 具有燃烧器的涡轮发动机，其包括围绕燃烧器衬套的中空壁。 燃烧器衬套包括面向内朝向燃烧室的内表面。 涡轮发动机包括朝向燃烧器的头端的中空壁沿上游方向的第一空气流动路径。 第一空气流动路径包括多个旁路开口，该旁路开口延伸穿过燃烧器衬套到内表面，以将第一冷却膜提供给燃烧器衬套的下游端部。 涡轮发动机还包括通过中空壁的与上游方向相反的第二方向的第二流动路径。 第二流路包括多个薄膜孔，其延伸穿过燃烧器衬套到内表面，以将第二冷却膜供应到第一冷却膜下游的燃烧器衬套的下游端部。

公开(公告)号：US20130031914A1

公开(公告)日：2013-02-07

申请号：US13195947

申请日：2011-08-02

申请人： Ching-Pang Lee ,  Jay A. Morrison

发明人： Ching-Pang Lee ,  Jay A. Morrison

IPC分类号： F02C7/12

CPC分类号： F01D5/186 ,  F01D9/023 ,  F01D25/12 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/00017 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y10S165/908

摘要： A system for cooling a wall (24) of a component having an outer surface with raised ribs (12) defining a structural pocket (10), including: an inner wall (26) within the structural pocket and separating the wall outer surface within the pocket into a first region (28) outside of the inner wall and a second region (40) enclosed by the inner wall; a plate (14) disposed atop the raised ribs and enclosing the structural pocket, the plate having a plate impingement hole (16) to direct cooling air onto an impingement cooled area (38) of the first region; a cap having a skirt (50) in contact with the inner wall, the cap having a cap impingement hole (20) configured to direct the cooling air onto an impingement cooled area (44) of the second region, and; a film cooling hole (22) formed through the wall in the second region.

摘要翻译： 一种用于冷却具有外表面的部件的壁（24）的系统，所述外壁具有限定结构袋（10）的凸肋（12），包括：在所述结构袋内的内壁（26），并将所述壁外表面分开 口袋进入内壁外部的第一区域（28）和被内壁包围的第二区域（40）; 设置在所述凸肋顶部并包围所述结构袋的板（14），所述板具有板冲击孔（16），以将冷却空气引导到所述第一区域的冲击冷却区域（38）上; 具有与所述内壁接触的裙部（50）的盖，所述盖具有盖冲击孔（20），所述盖冲击孔构造成将所述冷却空气引导到所述第二区域的冲击冷却区域（44）上; 在所述第二区域中穿过所述壁形成的薄膜冷却孔（22）。

公开(公告)号：US20130031908A1

公开(公告)日：2013-02-07

申请号：US13204369

申请日：2011-08-05

申请人： Richard Martin DiCintio ,  Patrick Benedict Melton ,  Lucas John Stoia

发明人： Richard Martin DiCintio ,  Patrick Benedict Melton ,  Lucas John Stoia

IPC分类号： F23R3/48

CPC分类号： F23R3/06 ,  F23R3/283 ,  F23R3/346 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/03044

摘要： A transfer tube for use in a late lean injection system of a combustor, wherein the combustor includes an inner radial wall, which defines a primary combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall forming a flow annulus therebetween, the outer radial wall including a late lean nozzle, the transfer tube including flow directing structure that defines a fluid passageway. At a first end, the flow directing structure may include an inlet and attachment means that attach the transfer tube to the late lean nozzle. The flow directing structure may have a configuration such that the fluid passageway spans the flow annulus and positions the outlet at a desirable injection point in the inner radial wall.

摘要翻译： 一种用于燃烧器的后期稀薄注射系统的转移管，其中所述燃烧器包括限定主燃料喷嘴下游的初级燃烧室的内部径向壁和围绕形成的内部径向壁的外部径向壁 其间的流动环空，所述外部径向壁包括后倾斜的喷嘴，所述输送管包括限定流体通道的流动引导结构。 在第一端，流动引导结构可以包括将传送管附接到后部稀薄喷嘴的入口和附接装置。 流动引导结构可以具有这样的构造，使得流体通道跨越流动环空并将出口定位在内部径向壁中期望的注入点。

公开(公告)号：US20130025287A1

公开(公告)日：2013-01-31

申请号：US13193686

申请日：2011-07-29

申请人： Frank J. Cunha

发明人： Frank J. Cunha

IPC分类号： F23R3/42 ,  F02C7/12

CPC分类号： F23R3/002 ,  F23R3/06 ,  F23R2900/00018 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

摘要： A combustor component of a gas turbine engine includes a refractory metal core (RMC) microcircuit for self-regulating a cooling flow.

摘要翻译： 燃气涡轮发动机的燃烧器部件包括用于自调节冷却流的难熔金属芯（RMC）微电路。

公开(公告)号：US08359866B2

公开(公告)日：2013-01-29

申请号：US12700453

申请日：2010-02-04

申请人： James A. Dierberger ,  Masamichi Hongoh ,  Dennis J. Sullivan

发明人： James A. Dierberger ,  Masamichi Hongoh ,  Dennis J. Sullivan

IPC分类号： F02C1/00

CPC分类号： F23M5/02 ,  F23M2900/05005 ,  F23R3/002 ,  F23R3/04 ,  F23R2900/00012 ,  F23R2900/03042 ,  F23R2900/03044

摘要： A combustor liner segment seal member is provided that includes a center section, a forward flange, and an aft flange. The center section includes a base surface, a gas path surface, a forward side surface, and an aft side surface. The forward flange extends outwardly from the forward side surface, and includes a width, a height, a shell side surface, and a liner side surface. The aft flange extends outwardly from the aft side surface, and includes a width, a height, a shell side surface, and a liner side surface.

摘要翻译： 提供了一种燃烧器衬套段密封件，其包括中心部分，前凸缘和后凸缘。 中心部分包​​括基面，气体路径表面，前侧表面和后侧表面。 前凸缘从前侧表面向外延伸，并且包括宽度，高度，壳侧表面和衬里侧表面。 后凸缘从后侧表面向外延伸，并且包括宽度，高度，壳侧表面和衬里侧表面。

公开(公告)号：US08359865B2

公开(公告)日：2013-01-29

申请号：US12700434

申请日：2010-02-04

申请人： James A. Dierberger ,  Dennis J. Sullivan

发明人： James A. Dierberger ,  Dennis J. Sullivan

IPC分类号： F02C1/00

CPC分类号： F23R3/04 ,  F23M5/02 ,  F23M5/04 ,  F23M2900/05005 ,  F23R3/002 ,  F23R2900/00012 ,  F23R2900/03042 ,  F23R2900/03044

摘要： A combustor for a gas turbine engine is provided that includes a support shell, a forward liner segment, an aft liner segment, and a seal member. The support shell has an interior surface, and exterior surface, and a plurality of impingement apertures disposed within the shell. The forward liner segment and aft liner segment are attached to the inner surface of the shell. The forward liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The aft liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The forward liner segment and the aft liner segment are separated from one another by a gap. The seal member is disposed within the gap. At least some of the plurality of impingement apertures disposed within the shell are aligned with the seal member and oriented to direct cooling air to impinge on the seal member.

摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器，其包括支撑壳体，前部衬套段，后部衬套段和密封构件。 支撑壳体具有内表面和外表面以及设置在壳体内的多个冲击孔。 前部衬垫段和后部衬套段连接到壳体的内表面。 前部衬垫段具有在面部表面和后表面之间延伸的边缘表面和密封肩部。 后排衬垫段具有在面部表面和后表面之间延伸的边缘表面和密封肩部。 前部衬垫段和后部衬套段通过间隙彼此分开。 密封构件设置在间隙内。 设置在壳体内的多个冲击孔中的至少一些撞击孔与密封构件对齐并且定向成引导冷却空气撞击密封构件。

公开(公告)号：US20120304659A1

公开(公告)日：2012-12-06

申请号：US13589375

申请日：2012-08-20

申请人： Matthew Paul Berkebile ,  Jerome David Brown ,  Ronald James Chila ,  Patrick Benedict Melton ,  Russell DeForest ,  David William Cihlar ,  Wei Chen ,  John Drake Vanselow

发明人： Matthew Paul Berkebile ,  Jerome David Brown ,  Ronald James Chila ,  Patrick Benedict Melton ,  Russell DeForest ,  David William Cihlar ,  Wei Chen ,  John Drake Vanselow

IPC分类号： F23R3/02 ,  G06F17/50 ,  F02C7/12

CPC分类号： F01D9/023 ,  F05D2260/201 ,  F23R3/06 ,  F23R2900/03044

摘要： An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, the impingement sleeve includes a body configured to at least partially surround a transition piece of the combustor. The impingement sleeve further includes a plurality of cooling holes defined in the body, the plurality of cooling holes having a cooling hole pattern configured to provide a desired operational value for the transition piece. At least one of the plurality of cooling holes has a chamfer extending at least partially between an inlet and an outlet of the at least one of the plurality of cooling holes. At least a portion of the plurality of cooling holes are generally longitudinally asymmetric.

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，冲击套筒包括构造成至少部分地围绕燃烧器的过渡件的主体。 所述冲击套筒还包括限定在所述主体中的多个冷却孔，所述多个冷却孔具有冷却孔图案，所述冷却孔图案被配置为为所述过渡件提供期望的操作值。 多个冷却孔中的至少一个具有至少部分地在所述多个冷却孔中的至少一个冷却孔的入口和出口之间延伸的倒角。 多个冷却孔的至少一部分大体上是纵向不对称的。

公开(公告)号：US08281597B2

公开(公告)日：2012-10-09

申请号：US12347165

申请日：2008-12-31

申请人： Shui-Chi Li ,  Mark Anthony Mueller ,  Michael Louis Vermeersch ,  Timothy James Held

发明人： Shui-Chi Li ,  Mark Anthony Mueller ,  Michael Louis Vermeersch ,  Timothy James Held

IPC分类号： F02C1/00

CPC分类号： F23R3/286 ,  F23R3/14 ,  F23R3/20 ,  F23R3/343 ,  F23R2900/03044 ,  Y02T50/675

摘要： A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder.

摘要翻译： 燃烧器旋流杯包括由管状中心体分开的同心的内旋流器和外旋流器。 中心体包括围绕内旋流器的旁路入口，并沿着穿孔内喷嘴向后分叉，以终止于环形火焰稳定器。 冲击环与火焰稳压器间隔开，与旁路入口流动连通，以从其中接收冷却空气，以冲击冷却火焰稳定器。

公开(公告)号：US20120227373A1

公开(公告)日：2012-09-13

申请号：US13509815

申请日：2010-11-15

申请人： Jacques Marcel Arthur Bunel ,  Mario Cesar De Sousa ,  Guillaume Sevi

发明人： Jacques Marcel Arthur Bunel ,  Mario Cesar De Sousa ,  Guillaume Sevi

IPC分类号： F02C7/266

CPC分类号： F23R3/06 ,  F02C7/266 ,  F05D2260/30 ,  F23D2207/00 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/03044 ,  Y02T50/675

摘要： A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.

摘要翻译： 一种燃气涡轮发动机的燃烧室，其包括壁，井壁固定，形成用于引导到燃烧室中的火花塞的凹部的井以及安装在井上的火花塞导向件相对于 井的轴线，火花塞引导件包括用于引导和支撑火花塞的圆柱形壁部分和安装成可滑动地与井的支承表面接合的密封环。 在燃烧室中，火花塞引导件包括具有用于将冷却空气供应到腔室的开口的冷却室。

公开(公告)号：US20120198854A1

公开(公告)日：2012-08-09

申请号：US13023710

申请日：2011-02-09

申请人： Reinhard Schilp ,  Muzaffer Sutcu

发明人： Reinhard Schilp ,  Muzaffer Sutcu

IPC分类号： F23R3/46

CPC分类号： F23R3/06 ,  F23M20/005 ,  F23R3/002 ,  F23R2900/00014 ,  F23R2900/03042 ,  F23R2900/03044

摘要： A combustor liner has a plurality of resonators formed thereon. Each resonator has a radially outer wall and at least one side wall. The outer wall can be free of holes. Each resonator has an inner cavity defined between the outer wall, the at least one side wall and the outer peripheral surface of the liner. The at least one side wall of each resonator surrounds a subset of a plurality of holes that extend substantially radially through the liner. A plurality of cooling passages extends generally longitudinally within the liner. Each cooling passage has an inlet in fluid communication with the exterior of the liner and an outlet in fluid communication with the inner cavity of a respective one of the resonators. A coolant, such as compressor air, can enter and flow along the cooling passages to thereby cool the liner and purge the inner cavity of the resonator.

摘要翻译： 燃烧器衬套具有形成在其上的多个谐振器。 每个谐振器具有径向外壁和至少一个侧壁。 外壁可以没有孔。 每个谐振器具有限定在外壁，至少一个侧壁和衬套的外周表面之间的内腔。 每个谐振器的至少一个侧壁围绕基本上径向延伸穿过衬垫的多个孔的子集。 多个冷却通道在衬套内大致纵向延伸。 每个冷却通道具有与衬套的外部流体连通的入口和与相应一个谐振器的内腔流体连通的出口。 诸如压缩机空气的冷却剂可以沿着冷却通道进入和流动，从而冷却衬管并吹扫谐振器的内腔。