公开(公告)号：SG11201404364TA

公开(公告)日：2014-10-30

申请号：SG11201404364T

申请日：2013-03-25

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D25/08 ,  F01D5/18 ,  F01D9/06 ,  F02C7/12

Abstract: 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.

公开(公告)号：EP2834498A4

公开(公告)日：2016-07-06

申请号：EP13772338

申请日：2013-03-25

Applicant: UNITED TECHNOLOGIES CORP

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

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

CPC classification number: F01D25/246 ,  F01D25/14 ,  F05D2240/81

Abstract: 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.

Abstract translation: 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：EP2885519A4

公开(公告)日：2016-06-08

申请号：EP13829409

申请日：2013-08-13

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02C7/00 ,  F02C7/14

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

Abstract: 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.

Abstract translation: 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

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/18 ,  F01D9/04

CPC classification number: 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

Abstract: 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.

Abstract translation: 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。