公开(公告)号：US20160333699A1

公开(公告)日：2016-11-17

申请号：US15110904

申请日：2014-12-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James B. Downey, JR. ,  Brenda Zhang ,  Steven G. Lemieux ,  Eleanor D. Kaufman ,  Takao Fukuda ,  Daniel C. Nadeau

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

CPC classification number: F01D5/18 ,  F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/2214 ,  Y02T50/676 ,  Y02T50/6765

Abstract: An airfoil for a gas turbine engine includes pressure and suction surfaces that are provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extending to the trailing edge. The cooling passage terminates in a trailing edge exit that is arranged in the trailing edge. Multiple rows of pedestals include a first row of pedestals that join the pressure and suction walls. The first row of pedestals is arranged closest to the trailing edge but interiorly from the trailing edge thereby leaving the trailing edge exit unobstructed.

Abstract translation: 用于燃气涡轮发动机的翼型件包括压力和抽吸表面，压力和吸力表面由沿径向延伸并在前缘和后缘连接的压力和吸力壁提供。 冷却通道设置在压力和吸力壁之间并延伸到后缘。 冷却通道终止于设置在后缘的后缘出口。 多排基座包括连接压力和吸力壁的第一排基座。 基座的第一排布置成最靠近后缘，但是位于后缘的内部，从而使后缘离开不受阻碍。

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.

公开(公告)号：US20160298470A1

公开(公告)日：2016-10-13

申请号：US14681195

申请日：2015-04-08

Applicant: United Technologies Corporation

Inventor： Takao Fukuda ,  Scott D. Hartmann

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F01D5/141 ,  F01D9/041 ,  F05D2230/21 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2240/129 ,  F05D2250/713 ,  F05D2250/74 ,  Y02T50/673

Abstract: An airfoil cluster includes an inner diameter platform and an outer diameter platform. A plurality of airfoils extend radially from the inner diameter platform to the outer diameter platform. Each airfoil has a leading edge and a trailing edge, and pressure and suction sides between the leading and trailing edges. At least one of the airfoils includes a recessed portion on the pressure side adjacent to the trailing edge.

Abstract translation: 翼型群包括内径平台和外径平台。 多个翼型件从内径平台径向延伸到外径平台。 每个翼型件具有前缘和后缘，并且在前缘和后缘之间的压力和吸力侧。 至少一个翼型件包括在靠近后缘的压力侧的凹部。