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公开(公告)号：US20110259017A1
公开(公告)日：2011-10-27
申请号：US12765372
申请日：2010-04-22
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F02C7/12 , F05D2230/11 , F05D2230/13 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface of the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.
摘要翻译： 公开了一种用于热气路径部件的冷却系统。 冷却系统可以包括组件层和覆盖层。 组件层可以包括第一内表面和第二外表面。 第二外表面可以限定多个通道。 组件层可以进一步限定大体上在第一内表面和第二外表面之间延伸的多个通道。 多个通道中的每一个可以流体地连接到多个通道中的至少一个。 覆盖层可以位于邻近部件层的第二外表面处。 多个通道可以被配置成将冷却介质流动到多个通道并且向覆盖层提供冲击冷却。 多个通道可以被配置成流过冷却介质，冷却覆盖层。
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公开(公告)号：US20110225947A1
公开(公告)日：2011-09-22
申请号：US12725602
申请日：2010-03-17
摘要： A combustor assembly of a turbine engine is provided with a mechanical air regulation unit which selectively varies the amount of air being delivered into a combustion zone of the combustor based upon a pressure of a fuel being supplied to the combustor. A first type of air regulation unit would act to increase the amount of air entering the combustion zone when greater amounts of a high heat value fuel are being delivered to the fuel nozzles of the combustor. A second type of air regulation unit could act to decrease the amount of air entering the combustion zone when greater amounts of a low heat value fuel are being delivered into the combustor through fuel nozzles.
摘要翻译： 涡轮发动机的燃烧器组件设置有机械空气调节单元，其基于供应到燃烧器的燃料的压力选择性地改变被输送到燃烧器的燃烧区域中的空气量。 当更大量的高热值燃料被输送到燃烧器的燃料喷嘴时，第一类型的空气调节单元将用于增加进入燃烧区域的空气量。 当较大量的低热值燃料通过燃料喷嘴输送到燃烧器中时，第二类型的空气调节单元可以起到减少进入燃烧区域的空气量的作用。
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公开(公告)号：US20110185572A1
公开(公告)日：2011-08-04
申请号：US12697005
申请日：2010-01-29
申请人： Bin Wei , Jon Conrad Schaeffer , Ronald Scott Bunker , Wenwu Zhang , Kathleen Blanche Morey , Jane Marie Lipkin , Benjamin Paul Lacy , Wilbur Douglas Scheidt
发明人： Bin Wei , Jon Conrad Schaeffer , Ronald Scott Bunker , Wenwu Zhang , Kathleen Blanche Morey , Jane Marie Lipkin , Benjamin Paul Lacy , Wilbur Douglas Scheidt
CPC分类号： F02C7/18 , B23K26/0624 , B23K26/082 , B23K26/384 , B23K26/389 , B23K26/60 , B23K26/702 , B23K2101/001 , B23K2101/34 , F01D25/12 , F05D2230/00 , F05D2230/13 , Y10T29/49316 , Y10T29/4932 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341 , Y10T29/49348 , Y10T29/49799
摘要： A process and system are provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.
摘要翻译： 提供了用于形成诸如用于涡轮叶片的成形气孔的过程和系统。 本公开的方面涉及使用短脉冲激光器形成空气孔的成形部分，形成与每个成形部分相对应的计量孔，并且使用短脉冲激光单独精加工成形部分。 在其他实施例中，可以改变这些操作的顺序，诸如形成成形部分，并且在形成相应的计量孔之前使用短脉冲激光来完成成形部分。
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64.发明申请MULTI-TUBE THERMAL FUSE FOR NOZZLE PROTECTION FROM A FLAME HOLDING OR FLASHBACK EVENT 有权多管式保险丝，用于从火焰保持或闪回事件中进行喷嘴保护公开(公告)号：US20100139280A1
公开(公告)日：2010-06-10
申请号：US12260451
申请日：2008-10-29
CPC分类号： F23R3/286 , F23D14/82 , F23D2900/00018 , Y10T29/49433
摘要： A protection system for a pre-mixing apparatus for a turbine engine, includes: a main body having an inlet portion, an outlet portion and an exterior wall that collectively establish a fuel delivery plenum; and a plurality of fuel mixing tubes that extend through at least a portion of the fuel delivery plenum, each of the plurality of fuel mixing tubes including at least one fuel feed opening fluidly connected to the fuel delivery plenum; at least one thermal fuse disposed on an exterior surface of at least one tube, the at least one thermal fuse including a material that will melt upon ignition of fuel within the at least one tube and cause a diversion of fuel from the fuel feed opening to at least one bypass opening. A method and a turbine engine in accordance with the protection system are also provided.
摘要翻译： 一种用于涡轮发动机的预混合装置的保护系统，包括：主体，其具有共同建立燃料输送增压室的入口部分，出口部分和外壁; 以及多个燃料混合管，其延伸穿过所述燃料输送室的至少一部分，所述多个燃料混合管中的每一个包括流体连接到所述燃料输送室的至少一个燃料供给开口; 至少一个热熔丝设置在至少一个管的外表面上，所述至少一个热熔丝包括将在所述至少一个管内的燃料点燃时熔化的材料，并导致燃料从所述燃料供给口转向 至少一个旁路开口。 还提供了根据保护系统的方法和涡轮发动机。
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公开(公告)号：US09382810B2
公开(公告)日：2016-07-05
申请号：US13560042
申请日：2012-07-27
CPC分类号： F01D25/12 , F01D9/065 , F05D2250/14 , F05D2250/75
摘要： A system for removing heat from a gas turbine generally includes a plurality of stationary nozzles arranged in an annular array within the gas turbine. Each of the plurality of stationary nozzles may include a radially outer platform and a radially extending cooling passage. The radially extending cooling passage may have an inlet that extends generally axially and circumferentially across a portion of the radially outer platform. A closed loop cooling coil may extend continuously circumferentially around the radially outer platform of two or more of the plurality of stationary nozzles. The closed loop cooling coil may be disposed circumferentially across and outside of the inlet of the radially extending cooling passage of each of the two or more stationary nozzles, and a cooling medium may flow through the cooling coil and out of the gas turbine so as to remove heat from the gas turbine.
摘要翻译： 用于从燃气涡轮机去除热量的系统通常包括在燃气涡轮机内布置成环形阵列的多个固定喷嘴。 多个固定喷嘴中的每一个可以包括径向外部平台和径向延伸的冷却通道。 径向延伸的冷却通道可以具有大致轴向和周向延伸穿过径向外部平台的一部分的入口。 闭环冷却盘管可围绕多个固定喷嘴中的两个或更多个的径向外部平台周向延伸。 闭环冷却盘管可以沿两个或多个固定喷嘴中的每一个的径向延伸的冷却通道的入口周向设置，并且冷却介质可以流过冷却盘管并流出燃气轮机，从而 从燃气轮机去除热量。
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公开(公告)号：US09151179B2
公开(公告)日：2015-10-06
申请号：US13086279
申请日：2011-04-13
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F05D2230/90 , F05D2240/14 , F05D2250/185 , F05D2260/204 , Y02T50/676 , Y10T29/49229
摘要： The present embodiments are generally directed toward systems and methods for cooling one or more shroud segments of a gas turbine engine. For example, in a first embodiment, a shroud segment is provided that is configured to at least partially surround a turbine blade of a turbine engine. The shroud segment includes a body and a microchannel disposed in the body. The microchannel is configured to flow a cooling fluid through the body.
摘要翻译： 本实施例通常涉及用于冷却燃气涡轮发动机的一个或多个护罩段的系统和方法。 例如，在第一实施例中，提供了构造成至少部分地围绕涡轮发动机的涡轮叶片的护罩段。 护罩区段包括主体和设置在身体中的微通道。 微通道构造成使冷却流体流过身体。
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公开(公告)号：US20130287546A1
公开(公告)日：2013-10-31
申请号：US13456407
申请日：2012-04-26
IPC分类号： F01D25/26
CPC分类号： F01D5/00 , F01D5/08 , F01D5/084 , F01D5/225 , F01D25/12 , F01D25/14 , F01D25/26 , F05D2260/201 , F05D2260/204
摘要： A turbine shroud cooling assembly for a gas turbine system includes an outer shroud component disposed within a turbine section of the gas turbine system and proximate a turbine section casing, wherein the outer shroud component includes at least one airway for ingesting an airstream. Also included is an inner shroud component disposed radially inward of, and fixedly connected to, the outer shroud component, wherein the inner shroud component includes a plurality of microchannels extending in at least one of a circumferential direction and an axial direction for cooling the inner shroud component with the airstream from the at least one airway.
摘要翻译： 用于燃气涡轮机系统的涡轮机罩冷却组件包括设置在燃气涡轮机系统的涡轮机部分内并且靠近涡轮部分壳体的外护罩部件，其中外护罩部件包括用于摄取气流的至少一个气道。 还包括内护罩部件，其设置在外护罩部件的径向内侧并且固定地连接到外护罩部件上，其中内护罩部件包括沿圆周方向和轴向方向中的至少一个延伸的多个微通道，用于冷却内护罩 具有来自至少一个气道的气流的部件。
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公开(公告)号：US20130183165A1
公开(公告)日：2013-07-18
申请号：US13349852
申请日：2012-01-13
申请人： Benjamin Paul Lacy
发明人： Benjamin Paul Lacy
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2240/303 , F05D2240/81 , F05D2250/324 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil includes a platform and an exterior surface connected to the platform. A plurality of trench segments are on the exterior surface, and a single cooling passage in each trench segment supplies a cooling media to the exterior surface.
摘要翻译： 翼型件包括平台和连接到平台的外表面。 多个沟槽段在外表面上，并且每个沟槽段中的单个冷却通道将冷却介质供应到外表面。
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公开(公告)号：US20130115103A1
公开(公告)日：2013-05-09
申请号：US13292432
申请日：2011-11-09
CPC分类号： F01D5/186 , Y10T29/49336
摘要： An article is disclosed that comprises a thermal material having a first surface and a second surface. The thermal material defines a film hole between the first surface and the second surface, and the film hole includes a metering portion adjacent the first surface and a diffuser portion adjacent the second surface. The metering portion defines a metering hole axis, and the diffuser portion defines a trench. The trench extends substantially parallel to a metering hole axis.
摘要翻译： 公开了一种包括具有第一表面和第二表面的热材料的制品。 热材料在第一表面和第二表面之间限定一个薄膜孔，薄膜孔包括邻近第一表面的计量部分和邻近第二表面的扩散器部分。 计量部分限定计量孔轴，并且扩散器部分限定沟槽。 沟槽基本上平行于计量孔轴线延伸。
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70.发明申请Plating of ceramic matrix composite parts as joining method in gas turbine hardware 审中-公开陶瓷基复合材料电镀作为燃气轮机硬件的接合方法公开(公告)号：US20120210718A1
公开(公告)日：2012-08-23
申请号：US12929878
申请日：2011-02-22
IPC分类号： F23R3/42 , C23C16/00 , B32B37/00 , F04D29/38 , B32B3/10 , B32B3/30 , B32B15/04 , B23K31/02 , C25D5/02
CPC分类号： B23K31/02 , B23K1/0018 , B23K35/007 , B23K35/0233 , B23K35/3033 , B23K2101/001 , B23K2101/34 , B23K2103/18 , B23K2103/26 , B23K2103/52 , C04B37/026 , C04B2237/123 , C04B2237/38 , C04B2237/40 , C04B2237/592 , C04B2237/597 , C04B2237/72 , C04B2237/76 , C04B2237/84 , C23C18/165 , C25D5/54 , F01D5/282 , F01D5/284 , F05D2300/6033 , Y10T156/10 , Y10T428/12486 , Y10T428/24612 , Y10T428/24917
摘要： Method of joining a ceramic matrix composite article to a metallic component by providing the ceramic matrix composite article with a metallic region which bonds to the metallic component.
摘要翻译： 通过向陶瓷基复合制品提供与金属组分结合的金属区域将陶瓷基复合材料制品与金属组分接合的方法。
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