公开(公告)号：EP2900962A4

公开(公告)日：2015-09-30

申请号：EP13841073

申请日：2013-09-26

申请人： UNITED TECHNOLOGIES CORP ,  BOEKE MARK A ,  GREGG SHAWN J ,  RILEY SARAH ,  DEGRAY JEFFREY J ,  SALZILLO RICHARD M

发明人： BOEKE MARK A ,  GREGG SHAWN J ,  RILEY SARAH ,  DEGRAY JEFFREY J ,  SALZILLO RICHARD M

IPC分类号： F01D5/18 ,  F01D9/02 ,  F01D25/08 ,  F01D25/12 ,  F01D25/24

CPC分类号： F01D5/186 ,  F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F01D25/246 ,  F05D2240/12 ,  F05D2240/81 ,  F05D2260/204 ,  Y02T50/672 ,  Y02T50/676

摘要： A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.

公开(公告)号：EP2855857A4

公开(公告)日：2016-06-08

申请号：EP13829503

申请日：2013-06-04

申请人： UNITED TECHNOLOGIES CORP

发明人： LUTJEN PAUL M ,  GREGG SHAWN J ,  DABBS THURMAN CARLO ,  BLANEY KEN F ,  KEENE RUSSELL E ,  CHICK BRUCE E

IPC分类号： F01D11/08 ,  F01D1/02 ,  F01D11/24 ,  F01D25/12 ,  F01D25/24

CPC分类号： F01D11/08 ,  F01D1/02 ,  F01D11/24 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/205 ,  F05D2260/2212 ,  F05D2260/2214

摘要： 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.

公开(公告)号：EP2900976A4

公开(公告)日：2015-11-11

申请号：EP13865075

申请日：2013-09-25

申请人： UNITED TECHNOLOGIES CORP

发明人： GREGG SHAWN J ,  LOW KEVIN J

IPC分类号： F02C7/22 ,  F02C3/14 ,  F02C9/26

CPC分类号： F02C3/14 ,  F23R3/28 ,  F23R3/50 ,  F23R2900/00014

公开(公告)号：EP3055091A4

公开(公告)日：2017-07-05

申请号：EP14851677

申请日：2014-09-25

申请人： UNITED TECHNOLOGIES CORP

发明人： GREGG SHAWN J ,  STAROSELSKY ALEXANDER ,  SRINIVASAN GAJAWALLI V

IPC分类号： B22F3/105 ,  B22F3/11 ,  B22F5/04 ,  F01D5/28

CPC分类号： B23K26/342 ,  B22F3/1055 ,  B22F3/11 ,  B22F5/04 ,  B22F2207/13 ,  B22F2207/17 ,  B23K26/0006 ,  B23K26/12 ,  B23K26/144 ,  B23K2203/02 ,  B23K2203/08 ,  B23K2203/14 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/18 ,  F01D5/28 ,  Y02P10/295

摘要： A method of forming a metal component having different regions containing different grain sizes and in porosities is by additive manufacturing. The method includes spreading a layer of starting powder on a temperature controlled moveable platform in a heated chamber with atmosphere and temperature control. Selected areas of the powder are melted and solidified with a computer controlled focused energy beam. The cooled platform is then indexed down and the process repeated. The grain size of the melted and solidified region can be controlled by the cooling rate during solidification which, in turn is controlled by the temperature of the chamber and the temperature of the cooled moveable platform.

摘要翻译： 形成具有不同粒度和孔隙度的不同区域的金属组分的方法是通过增材制造。 该方法包括在具有大气和温度控制的加热室中的温度控制的可移动平台上散布一层起始粉末。 选定的粉末区域通过计算机控制的聚焦能量束熔化并固化。 然后将冷却的平台索引下来并重复该过程。 熔化和凝固区域的晶粒尺寸可以通过凝固过程中的冷却速率来控制，凝固过程中的冷却速度又由腔室的温度和冷却的可移动平台的温度来控制。

公开(公告)号：EP2834498A4

公开(公告)日：2016-07-06

申请号：EP13772338

申请日：2013-03-25

申请人： UNITED TECHNOLOGIES CORP

发明人： BERGMAN RUSSELL J ,  GREGG SHAWN J ,  PAPPLE MICHAEL ,  LUTJEN PAUL M ,  CAPRARIO JOSEPH T ,  ENNACER MOHAMMED ,  DABBS THURMAN CARLO

IPC分类号： F02C7/12 ,  F01D5/18 ,  F01D25/08 ,  F01D25/14 ,  F01D25/24

CPC分类号： F01D25/246 ,  F01D25/14 ,  F05D2240/81

摘要： A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

摘要翻译： 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一增压室流体连通，并且与定子叶片的翼型内的第一翼型冷却通道形成流体连通。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。

公开(公告)号：EP2935833A4

公开(公告)日：2016-08-03

申请号：EP13863795

申请日：2013-12-18

申请人： UNITED TECHNOLOGIES CORP

发明人： CAPRARIO JOSEPH T ,  GREGG SHAWN J ,  HYLAND DAVE J

IPC分类号： F02C7/12 ,  F01D9/06 ,  F01D25/12 ,  F02K3/00

CPC分类号： F01D9/065 ,  F05D2260/22141 ,  Y02T50/676

摘要： 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.

摘要翻译： 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通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。

公开(公告)号：EP2900967A4

公开(公告)日：2015-09-16

申请号：EP13866792

申请日：2013-09-26

申请人： UNITED TECHNOLOGIES CORP ,  RILEY SARAH ,  BOEKE MARK A ,  DEGRAY JEFFREY J ,  GREGG SHAWN J

发明人： RILEY SARAH ,  BOEKE MARK A ,  DEGRAY JEFFREY J ,  GREGG SHAWN J

IPC分类号： F02C7/12 ,  F01D5/18 ,  F01D25/12

CPC分类号： F01D25/12 ,  F01D5/187 ,  F01D9/02 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2250/183 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/672 ,  Y02T50/676

摘要： 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.

公开(公告)号：EP2885519A4

公开(公告)日：2016-06-08

申请号：EP13829409

申请日：2013-08-13

申请人： UNITED TECHNOLOGIES CORP

发明人： PAPPLE MICHAEL LESLIE CLYDE ,  BERGMAN RUSSELL J ,  ENNACER MOHAMMED ,  GREGG SHAWN J ,  MONGILLO DOMINIC J

IPC分类号： F02C7/00 ,  F02C7/14

CPC分类号： F01D9/041 ,  F01D5/187 ,  F01D9/023 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/201 ,  F05D2260/22141 ,  Y02T50/676

摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.

摘要翻译： 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括具有第一路径侧和第二路径侧的平台以及设置在第一路径侧和第二路径侧中的一个上的平台冷却回路 平台的路径一侧。 平台冷却回路包括第一芯腔，与第一芯腔流体连通的空腔，以及定位成覆盖至少空腔的盖板。

公开(公告)号：EP2890880A4

公开(公告)日：2015-12-02

申请号：EP13832115

申请日：2013-08-26

申请人： UNITED TECHNOLOGIES CORP

发明人： GREGG SHAWN J ,  MONGILLO DOMINIC J ,  PAPPLE MICHAEL LESLIE CLYDE ,  BERGMAN RUSSELL J ,  ENNACER MOHAMMED

IPC分类号： F01D5/18 ,  F01D9/04

CPC分类号： F01D5/188 ,  F01D5/187 ,  F01D5/189 ,  F01D9/041 ,  F01D25/12 ,  F02C7/12 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/126 ,  F05D2240/30 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure including, 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.

摘要翻译： 根据本公开的示例性方面的用于燃气涡轮发动机的部件，其特征在于，包括在前缘和后缘之间延伸的翼型和设置在翼型内部的冷却回路。 所述冷却回路包括至少一个在所述翼型件内部延伸的芯腔，容纳在所述至少一个芯腔内的挡板，与所述至少一个芯腔相邻定位的多个基座和位于所述至少一个芯腔之间的第一多个轴向肋 多个基座和翼型件的后缘。

公开(公告)号：EP2900984A4

公开(公告)日：2015-09-30

申请号：EP13866122

申请日：2013-09-25

申请人： UNITED TECHNOLOGIES CORP

发明人： GREGG SHAWN J ,  OTERO EDWIN

IPC分类号： F02C9/22 ,  F01D17/16 ,  F02K1/30

CPC分类号： F02C3/14 ,  F01D9/02 ,  F05D2260/961 ,  F23R3/10 ,  F23R3/28 ,  F23R3/50 ,  F23R2900/00005 ,  F23R2900/00014 ,  Y02T50/675