公开(公告)号：US20160053621A1

公开(公告)日：2016-02-25

申请号：US14780573

申请日：2014-04-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ky H. Vu ,  Lisa P. O'Neill ,  Takao Fukuda ,  Gerald M. Mace, Jr. ,  Andy Turko ,  Andrew P. Boursy ,  Lynn M. Boy

IPC: F01D9/04 ,  F01D5/14

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：US10047617B2

公开(公告)日：2018-08-14

申请号：US14780573

申请日：2014-04-07

Applicant: United Technologies Corporation

Inventor： Ky H. Vu ,  Lisa P. O'Neill ,  Takao Fukuda ,  Gerald M. Mace, Jr. ,  Andy Turko ,  Andrew P. Boursy ,  Lynn M. Boy

IPC: F01D9/04 ,  F01D5/14

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.