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1. 发明公开

EP3149310A2 TURBINE ENGINE, COMPONENTS, AND METHODS OF COOLING SAME 审中-公开
标题翻译： TURBINENMOTOR，KOMPONENTEN UND VERFAHREN ZURKÜHLUNGDAVON
公开(公告)号：EP3149310A2
公开(公告)日：2017-04-05
申请号：EP15804640.9
申请日：2015-05-28
申请人： General Electric Company
发明人： MANNING, Robert Francis , STONE, Timothy Deryck , BUHLER, Jared Peter , CORRELA, Victor Hugo Silva , LASKOWSKI, Gregory Michael , MURRAY, Robert Carl , PROCTOR, Robert , RATZLAFF, Jonathan Russell , STARKWEATHER, John Howard , STOVER, Curtis Walton
IPC分类号： F02C7/05 , F02C7/052 , B01D45/16 , B04C3/00 , B04C3/06
CPC分类号： F01D25/32 , B01D45/16 , B04C3/00 , B04C3/06 , B04C2003/003 , B04C2003/006 , B64D33/08 , B64D2033/022 , B64D2033/024 , B64D2033/0246 , F01D5/08 , F01D25/12 , F02C3/04 , F02C7/05 , F02C7/052 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2240/35
摘要： A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.
摘要翻译：用于从流体流中除去颗粒的离心分离器包括配置成增加流体流的角速度的角速度增量器，配置成分离流体流以形成浓颗粒流和还原颗粒流的分流器，以及配置成接收所述还原颗粒物流的出口导管。一种用于涡轮发动机的导流器组件包括具有流动通道的导流器，该流动通道具有与发动机的涡轮机部分流体连通的导流器入口和导流器出口，以及颗粒分离器，其包括粒子聚集器，其从发动机的压缩机部分和分流器。涡轮发动机包括：冷却空气流回路，其将流体流供应到用于冷却的发动机的涡轮部分;位于冷却空气流动回路内的颗粒分离器;以及形成流体连通的冷却空气流动回路的一部分的导流器与颗粒分离器。一种用于冷却具有导流器的涡轮发动机的旋转叶片的方法包括将冷却流体流从涡轮发动机的一部分引向旋转叶片，通过使冷却流体流通过惯性分离器将颗粒与冷却流体流分离，从而加速从惯性分离器发射的减少粒子流到旋转叶片的速度，以及通过将来自惯性分离器的还原颗粒物流发射到导流器中的冷却通道来定向还原颗粒物流。

2. 发明公开

EP3149284A2 ENGINE COMPONENTS WITH IMPINGEMENT COOLING FEATURES 审中-公开
标题翻译： MOTOROMPONENTEN MITPRALLKÜHLUNGSFUNKTIONEN
公开(公告)号：EP3149284A2
公开(公告)日：2017-04-05
申请号：EP15804994.0
申请日：2015-05-27
申请人： General Electric Company
发明人： STOVER, Curtis, Walton , RAUSCH, Jonathan, Michael , ATSUCHI, Satoshi , BRAINCH, Gulcharan, Singh , BRIGGS, Robert, David , BUNKER, Ronald, Scott , KULKARNI, Ambarish, Jayant , MEADE, Michael, Alan , PRITCHARD, Byron, Andrew , PROCTOR, Robert
IPC分类号： F01D5/18
CPC分类号： F02C7/18 , F01D5/189 , F01D9/041 , F01D11/08 , F01D25/12 , F05D2240/81 , F05D2250/38 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , F05D2260/607 , F23R3/002 , F23R3/005 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/673 , Y02T50/676
摘要： Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.
摘要翻译：提供了燃气涡轮发动机部件，其利用插入件沿着发动机部件的冷却表面提供冷却空气。插入件提供面向发动机部件的冷却侧表面的冷却孔或孔，并将冷却空气直接导入该冷却侧表面。孔可以以阵列形式并且以与插入件的表面成倾斜或非正交的角度定向并且可以与被冷却的发动机部件的表面成一角度。发动机部件组件设置有逆流冲击冷却，包括在一侧具有冷却流体流动路径的发动机部件冷却表面和与第一部件相邻的第二部件。第二部件可以具有形成阵列的多个开口，其中开口以与第二部件的表面成非正交角度延伸穿过第二部件。

3. 发明公开

EP3168426A1 GAS TURBINE ENGINE WITH VANE HAVING A COOLING INLET 审中-公开
标题翻译：燃气轮机发动机叶片有冷却进气口
公开(公告)号：EP3168426A1
公开(公告)日：2017-05-17
申请号：EP16196837.5
申请日：2016-11-02
申请人： General Electric Company
发明人： SUBRAMANIAN, Sesha , SHELTON, Monty Lee , PROCTOR, Robert , THOPPIL, Mohamed Musthafa , GURRAM, Venkateswararao , JOINER, Josiah Warren , SAK, Wojciech
IPC分类号： F01D11/00 , F01D9/04 , F01D5/18 , F04D29/54
CPC分类号： F04D29/582 , F01D5/187 , F01D9/041 , F01D11/001 , F04D29/083 , F04D29/321 , F04D29/542 , F04D29/584 , F05D2220/3216 , F05D2240/81 , Y02T50/676
摘要： An apparatus and method of cooling a hot portion of a gas turbine engine 10, such as a multi-stage compressor 24, 26 of a gas turbine engine 10, by reducing an operating air temperature in a space 130 between a seal 128 and a blade post 112 of adjacent stages 52, 54 by routing cooling air through an inlet 140 in the vane, passing the routed cooling air through the vane 62, and emitting the routed cooling air into the space 130.
摘要翻译：通过降低密封件128与叶片之间的空间130中的操作空气温度来冷却燃气涡轮发动机10的热部分（例如燃气涡轮发动机10的多级压缩机24,26）的装置和方法通过引导冷却空气通过叶片中的入口140，使路由的冷却空气穿过叶片62并且将经路由的冷却空气发射到空间130中来使相邻的级52,54的柱112接近。

4. 发明公开

EP2923041A1 TURBINE SHROUD MOUNTING AND SEALING ARRANGEMENT 审中-公开
标题翻译：涡轮式安装和密封装置
公开(公告)号：EP2923041A1
公开(公告)日：2015-09-30
申请号：EP13818856.0
申请日：2013-10-15
申请人： General Electric Company
发明人： ALBERS, Joseph, Charles , PROCTOR, Robert , SHELTON, Monty, Lee , RUSSO, Richard, Jr.
IPC分类号： F01D5/22 , F01D11/12
CPC分类号： F01D25/28 , F01D5/12 , F01D5/225 , F01D11/122 , F01D11/127
摘要： A turbine shroud apparatus for a gas turbine engine having a centerline axis includes: a shroud segment having: an arcuate body extending axially between forward and aft ends and laterally between opposed end faces, wherein each of the end faces includes seal slots formed therein; and an arcuate stationary seal member mounted to the body; a turbine vane disposed axially aft of the shroud segment; and a casing surrounding the shroud segment and the turbine vane; wherein the turbine vane is mounted to the case so as to bear against the stationary seal member, compressing it and forcing the shroud segment radially outward against the casing.
摘要翻译：一种用于具有中心线轴线的燃气涡轮发动机的涡轮护罩装置，包括：护罩区段，该护罩区段具有：弓形主体，其在前端和后端之间轴向延伸并且在相对端面之间横向延伸，其中每个端面包括形成在其中的密封槽; 和一个安装在本体上的弧形静止密封件; 设置在所述护罩区段的轴向后方的静叶片; 以及围绕所述护罩区段和所述静叶片的壳体; 其中，所述涡轮叶片被安装到所述壳体以抵靠所述静止密封构件，压缩所述涡轮叶片并且迫使所述护罩区段径向向外地抵靠所述壳体。

5. 发明公开

EP3771644A1 VEHICLE HEAT EXCHANGER SYSTEM 审中-公开
公开(公告)号：EP3771644A1
公开(公告)日：2021-02-03
申请号：EP20186964.1
申请日：2020-07-21
申请人： General Electric Company
发明人： SCHIMMELS, Scott , RAMBO, Jeffrey , KUPISZEWSKI, Thomas , INTEMANN, Paul , PROCTOR, Robert
IPC分类号： B64D13/08 , B64C1/12 , B64C1/06 , B64C3/26 , B64D33/08 , B64C3/18 , B64C7/02 , B64D29/00 , B64D13/00 , B64D13/06
摘要： A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.

6. 发明公开

EP3187692A1 SYSTEMS AND METHODS FOR A COMPRESSOR DIFFUSION SLOT 审中-公开
标题翻译：用于压缩机扩散槽的系统和方法
公开(公告)号：EP3187692A1
公开(公告)日：2017-07-05
申请号：EP16206166.7
申请日：2016-12-22
申请人： General Electric Company
发明人： KLASING, Kevin Samuel , PROCTOR, Robert , RATZLAFF, Jonathan Russell , DOERFLEIN, Thomas Matthew
IPC分类号： F01D9/06 , F04D27/02 , F02C9/18
CPC分类号： F04D27/009 , F01D9/06 , F01D17/105 , F02C6/08 , F02C9/18 , F04D27/0215 , F04D27/023 , F04D29/321 , F04D29/522 , F04D29/542 , F04D29/545 , F04D29/547 , F05D2220/32 , F05D2230/60
摘要： A compressor (200) for a gas turbine engine (100) includes a stator and a rotor. The stator includes first and second stator vanes (202, 206) attached to first and second vane platforms (208, 210), respectively. The rotor includes a plurality of rotor blades (204) that rotate with respect to the stator. An inner stator casing (212) supports the first and second vane platforms (208, 210) and encloses the stator and the rotor. An outer stator casing (214) encloses the inner stator casing (212), and a bleed cavity (228) is disposed therebetween. At least one diffuser (216) is disposed between the first vane platform (208) and the second vane platform (210), and is configured to allow air communication between the inner stator casing (212) and the bleed cavity (228). An exit opening (226) of the diffuser (216) is disposed within the bleed cavity (228) at a location separate from the inner stator casing (212) and the outer stator casing (214).
摘要翻译：用于燃气涡轮发动机（100）的压缩机（200）包括定子和转子。定子包括分别附接到第一和第二叶片平台（208,210）的第一和第二定子叶片（202,206）。转子包括相对于定子旋转的多个转子叶片（204）。内定子壳体（212）支撑第一和第二叶片平台（208,210）并包围定子和转子。外定子壳体（214）包围内定子壳体（212），并且排放腔（228）设置在它们之间。至少一个扩散器（216）设置在第一叶片平台（208）和第二叶片平台（210）之间，并且构造成允许内定子壳体（212）和泄放腔（228）之间的空气连通。扩散器（216）的出口开口（226）在与内定子外壳（212）和外定子外壳（214）分开的位置处设置在泄放腔（228）内。

7. 发明公开

EP3149311A2 TURBINE ENGINE AND PARTICLE SEPARATORS THEREFORE 审中-公开
标题翻译：巴布亚新几内亚比索
公开(公告)号：EP3149311A2
公开(公告)日：2017-04-05
申请号：EP15804642.5
申请日：2015-05-29
申请人： General Electric Company
发明人： STONE, Timothy, Deryck , LASKOWSKI, Gregory, Michael , PROCTOR, Robert , STOVER, Curtis , MANNING, Robert, Francis , CORREIA, Victor, Hugo Silva , BUHLER, Jared, Peter , MURRAY, Robert, Carl , BOURASSA, Corey , PRITCHARD, Byron, Andrew, Jr. , RATZLAFF, Jonathan, Russell
IPC分类号： F02C7/05 , B01D45/16
CPC分类号： F02C7/05 , B01D45/16 , B04C3/00 , B04C3/06 , B04C2003/003 , B04C2003/006 , F01D25/12 , F02C7/12 , F05D2260/607 , Y02T50/675
摘要： A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.
摘要翻译：具有联接到涡轮机部分的旁路流体管道的涡轮发动机包括位于旁路流体管道内的至少一个颗粒分离器，以在旁路流到达涡轮部分之前将颗粒与旁路流体流分离以进行冷却。用于从流体流中除去颗粒的离心分离器包括角速度增量器，颗粒出口，角速度增量器下游的角速度减速器以及设置在角速度增量器和角速度减速器之间的弯道。

8. 发明公开

EP2971591A2 TURBINE SHROUD WITH SPLINE SEAL 审中-公开
标题翻译：与环绕密封条TURBINE
公开(公告)号：EP2971591A2
公开(公告)日：2016-01-20
申请号：EP14771643.5
申请日：2014-03-07
申请人： General Electric Company
发明人： ALBERS, Joseph, C. , SHELTON, Monty, Lee , PROCTOR, Robert , RUSSO, Richard, Jr.
IPC分类号： F01D11/12 , F02C7/28 , F01D11/00 , F01D25/24
CPC分类号： F01D11/122 , F01D11/005 , F01D11/127 , F01D25/246 , F02C7/28 , F05D2220/32 , F05D2240/11 , F05D2240/57 , Y02T50/671
摘要： A turbine shroud assembly comprises a honeycomb rub strip, a metallic backsheet disposed along an upper edge of said honeycomb seal structure, a shroud frame having a first rail and a second rail disposed at lateral edges of said metallic backsheet, a first support and a second support connected to the first rail and the second rail, a spline extending axially in the first rail and the second rail along laterally outer surfaces of the first rail and the second rail and, a spline seal having a first edge and a second opposite edge, the first edge disposed in each of the spline grooves and the second opposite edge being capable of positioning in an adjacent shroud assembly.

9. 发明公开

EP2885508A1 ACTIVE CLEARANCE CONTROL SYSTEM 审中-公开
标题翻译： ACTIVE分裂控制系统
公开(公告)号：EP2885508A1
公开(公告)日：2015-06-24
申请号：EP13733488.4
申请日：2013-06-19
申请人： General Electric Company
发明人： SCHIMMELS, Scott, Alan , FUSINATO, Daniel, John , GLESSNER, John, Carl , MIRKOVICH, Dan, Nicholas , PROCTOR, Robert
IPC分类号： F01D11/24
CPC分类号： F01D11/24 , F01D25/12 , F01D25/14 , F05D2200/33 , F05D2260/201 , F05D2260/30 , Y02T50/676
摘要： Active clearance control systems for gas turbine engines are disclosed. An example active clearance control system may include a generally circumferentially mounted spray tube comprising a plurality of impingement holes arranged to impinge thermal control air on a clearance control component of a case; a rigid mounting assembly substantially rigidly coupling the spray tube to the case; and/or a sliding mounting assembly coupling the spray tube to the case while permitting limited relative movement between the spray tube and the case in a direction generally parallel with an engine axis. The sliding mount may be coupled to the case generally axially forward of the rigid mount. A ratio of the stand-off distance to the impingement hole diameter may be less than about 8. A ratio of the arc spacing to the impingement hole diameter may be less than about 15.

10. 发明公开

EP2844838A1 TURBINE NOZZLE OUTER BAND AND AIRFOIL COOLING APPARATUS 审中-公开
标题翻译： TURBINENDÜSENAUSSENBANDUNDSCHAUFELKÜHLUNGSVORRICHTUNG
公开(公告)号：EP2844838A1
公开(公告)日：2015-03-11
申请号：EP13718279.6
申请日：2013-04-15
申请人： General Electric Company
发明人： ALLEN, Marshall, Scott , CORREIA, Victor Hugo, Silva , PROCTOR, Robert , BUHLER, Jared
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D9/041 , F01D5/189 , F01D25/00 , F05B2230/237 , F05D2240/81 , F05D2260/201 , Y02T50/676
摘要： A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.
摘要翻译：涡轮喷嘴段包括：弓形外带段; 所述翼型涡轮叶片从所述外带段径向向内延伸，所述涡轮叶片具有中空的内部; 碰撞挡板组件，其固定到所述外部带，以便与所述外部带段协调地限定冲击腔，其中所述冲击挡板组件具有形成在其中的至少一个冲击孔，所述至少一个冲击孔被布置成引导所述外部带段处的冷却空气; 以及至少一个冲击插入件，其具有形成在其中的至少一个冲击孔，其设置在涡轮叶片的内部，冲击插入件与冲击挡板组件中的开口配合，使得冲击挡板与冲击腔直接流体连通隔离。

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