公开(公告)号：WO2014209464A3

公开(公告)日：2015-03-12

申请号：PCT/US2014033148

申请日：2014-04-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： VU KY H ,  O'NEILL LISA P ,  FUKUDA TAKAO ,  MACE JR GERALD M ,  TURKO ANDY ,  BOURSY ANDREW P ,  BOY LNYY M

IPC: F01D9/02 ,  F01D5/14 ,  F01D25/08

CPC classification number: F01D9/041 ,  F01D5/14 ,  F01D5/143 ,  F05D2240/57 ,  F05D2240/81 ,  F05D2250/19 ,  F05D2250/192 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.

Abstract translation: 用于燃气涡轮发动机的翼型件包括平台。 机翼部件包括翼面延伸的流路表面。 横向延伸的后表面邻近流动通道表面。 波纹表面毗邻流路表面和后表面。 用于燃气涡轮发动机的翼型件包括平台。 机翼部件包括翼面延伸的流路表面。 横向延伸的后表面邻近流动通道表面。 波纹表面毗邻流路表面和后表面。 后表面在周向延伸的边缘处从第一后边缘延伸到第二后边缘。 轮廓表面从第一和第二边缘中的至少一个设置在内侧。

公开(公告)号：WO2015057309A3

公开(公告)日：2015-07-30

申请号：PCT/US2014053041

申请日：2014-08-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： VU KY H

IPC: F01D9/02 ,  F01D25/12

CPC classification number: F01D25/12 ,  F01D5/189 ,  F01D9/041 ,  F01D9/065 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/81 ,  F05D2260/201

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, and an insert positioned such that a first portion of the insert extends relative to a surface of the platform and a second portion extends inside the airfoil. A standoff supports the insert above the surface.

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平台，从平台延伸的翼型件，以及定位成使得插入件的第一部分相对于表面延伸的插入件 并且第二部分在翼型内部延伸。 支座支撑表面上的插入物。

公开(公告)号：EP3047111A4

公开(公告)日：2016-09-28

申请号：EP14854393

申请日：2014-08-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： VU KY H

IPC: F01D9/02 ,  F01D5/18 ,  F01D9/06 ,  F01D25/12

CPC classification number: F01D25/12 ,  F01D5/189 ,  F01D9/041 ,  F01D9/065 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/81 ,  F05D2260/201

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, and an insert positioned such that a first portion of the insert extends relative to a surface of the platform and a second portion extends inside the airfoil. A standoff supports the insert above the surface.

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包括平台，从平台延伸的翼型件和定位成使得插入件的第一部分相对于表面延伸的插入件 并且第二部分在翼型内部延伸。 支架支撑表面上方的插入物。

公开(公告)号：EP2986823A4

公开(公告)日：2016-07-20

申请号：EP14817409

申请日：2014-04-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： VU KY H ,  O'NEILL LISA P ,  FUKUDA TAKAO ,  MACE JR GERALD M ,  TURKO ANDY ,  BOURSY ANDREW P ,  BOY LNYY M

IPC: F01D9/02 ,  F01D5/14 ,  F01D25/08

CPC classification number: F01D9/041 ,  F01D5/14 ,  F01D5/143 ,  F05D2240/57 ,  F05D2240/81 ,  F05D2250/19 ,  F05D2250/192 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.

Abstract translation: 用于燃气涡轮发动机的翼型件包括平台。 翼型部件包括翼型件从其延伸的流路表面。 横向延伸的后表面邻近流动通道表面。 轮廓表面毗邻流路表面和后表面。 用于燃气涡轮发动机的翼型件包括平台。 翼型部件包括翼型件从其延伸的流路表面。 横向延伸的后表面邻近流动通道表面。 轮廓表面毗邻流路表面和后表面。 后表面在周向延伸的边缘处从第一后边缘延伸到第二后边缘。 轮廓表面从第一和第二边缘中的至少一个设置在内侧。