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公开(公告)号：US20150300195A1
公开(公告)日：2015-10-22
申请号：US14789232
申请日：2015-07-01
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Shawn J. Gregg , Thurman Carlo Dabbs , Ken F. Blaney , Russell E. Keene , Bruce E. Chick
CPC classification number: F01D11/08 , F01D1/02 , F01D11/24 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2260/20 , F05D2260/201 , F05D2260/205 , F05D2260/2212 , F05D2260/2214
Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.
Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封件包括壁，前钩和后钩。 该壁在前钩和后钩之间延伸，其适于将叶片外部空气密封件安装到燃气涡轮发动机的壳体上。 壁包括沿壁的至少一部分延伸的芯通道。 芯通道径向和轴向地延伸穿过后钩的一部分，以沿着后钩的后缘与一个或多个孔连通。
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Patent Agency Ranking
公开(公告)号：US20140178174A1
公开(公告)日：2014-06-26
申请号：US13724320
申请日：2012-12-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Joseph T. Caprario , Shawn J. Gregg , Dave J. Hyland
IPC: F01D9/02
CPC classification number: F01D9/065 , F05D2260/22141 , Y02T50/676
Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut. The flow passage is configured to direct air from the compressor to another portion of the gas turbine engine. The flow passage has at least one surface feature that at least partially hinders some airflow through the flow passage.
Abstract translation: 根据示例性实施例，燃气涡轮发动机组件尤其包括压缩机。 压缩机附近的支柱包括穿过支柱的一部分的流动通道。 流动通道构造成将空气从压缩机引导到燃气涡轮发动机的另一部分。 流动通道具有至少部分地阻碍通过流动通道的一些气流的至少一个表面特征。
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公开(公告)号：US11377965B2
公开(公告)日：2022-07-05
申请号：US15450087
申请日：2017-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
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公开(公告)号：US09476313B2
公开(公告)日：2016-10-25
申请号：US13724320
申请日：2012-12-21
Applicant: United Technologies Corporation
Inventor： Joseph T. Caprario , Shawn J. Gregg , Dave J. Hyland
CPC classification number: F01D9/065 , F05D2260/22141 , Y02T50/676
Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut. The flow passage is configured to direct air from the compressor to another portion of the gas turbine engine. The flow passage has at least one surface feature that at least partially hinders some airflow through the flow passage.
Abstract translation: 根据示例性实施例，燃气涡轮发动机组件尤其包括压缩机。 压缩机附近的支柱包括穿过支柱的一部分的流动通道。 流动通道构造成将空气从压缩机引导到燃气涡轮发动机的另一部分。 流动通道具有至少部分地阻碍通过流动通道的一些气流的至少一个表面特征。
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公开(公告)号：US20140093361A1
公开(公告)日：2014-04-03
申请号：US13630107
申请日：2012-09-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sarah Riley , Mark A. Boeke , Jeffrey J. DeGray , Shawn J. Gregg
CPC classification number: F01D25/12 , F01D5/187 , F01D9/02 , F05D2240/12 , F05D2240/126 , F05D2240/127 , F05D2240/81 , F05D2250/183 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.
Abstract translation: 用于燃气涡轮发动机的翼型件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 一个V形形状的跳闸条从一个长度的跳闸带高度从表面延伸到冷却通道中。 跳闸条高度沿长度变化。 用于燃气涡轮发动机的涡轮叶片包括内平台和外平台。 在内平台上设有冷却通道。 冷却通道由第一和第二径向延伸的腿部彼此周向间隔开并且通过周向通道彼此连接而设置。 一对翼型件从相同的内平台径向延伸。 跳闸条沿着一段长度以一个跳闸带高度从表面延伸到圆周通道中。 行程长度沿长度变化。
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公开(公告)号：US20140083111A1
公开(公告)日：2014-03-27
申请号：US13626523
申请日：2012-09-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shawn J. Gregg , Kevin K. Low
CPC classification number: F02C3/14 , F23R3/28 , F23R3/50 , F23R2900/00014
Abstract: A combustor of a gas turbine engine includes a multiple of fuel nozzles arranged asymmetrically
Abstract translation: 燃气涡轮发动机的燃烧器包括不对称排列的多个燃料喷嘴
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