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：EP2971585A4

公开(公告)日：2016-12-07

申请号：EP14767834

申请日：2014-03-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BANKS ANTON G ,  TURKO ANDY

IPC: F01D11/00 ,  F01D9/02 ,  F02C7/00

CPC classification number: F01D11/003 ,  F01D9/041 ,  F01D11/005 ,  F01D25/24 ,  F01D25/246 ,  F05D2240/12 ,  F05D2250/611 ,  F05D2260/941 ,  Y02T50/672

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。