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：JPH1122409A

公开(公告)日：1999-01-26

申请号：JP12192998

申请日：1998-05-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FUKUDA TAKAO ,  PRICE FRANCIS R ,  COOK CONAN P ,  HOFF RICHARD W ,  SINGER IRWIN D

IPC: F01D9/02 ,  F01D5/18 ,  F01D9/06 ,  F02C7/18

Abstract: PROBLEM TO BE SOLVED: To remove particulates from cooling air and efficiently cool a front edge region. SOLUTION: An air foil capable of cooling having a passage to blow out particulates brought by cooling air is opened. Various details of a structure supply cooling air to front edges 60, 69 of the air foil. A chord directional duct 100 is extended to an inlet of a rear part passage extending in the blade length direction passing through a supply passage 92 extending in the blade length direction, a part of cooling air and particulates from the duct 100 are directed to the inside of the rear passage through an inlet 72 of the supply passage 92 by amomemtum effect, and most of a flow of cooling air is directed to the supply passage 92 to cool the front edges 60, 69 of the air foil.

公开(公告)号：DE69826367D1

公开(公告)日：2004-10-28

申请号：DE69826367

申请日：1998-06-26

Applicant: UNITED TECHNOLOGIES CORP HARTF

Inventor： FUKUDA TAKAO ,  PRICE FRANCIS R ,  COOK CONAN P ,  HOFF RICHARD W ,  SINGER IRWIN D

IPC: F01D9/02 ,  F01D5/18 ,  F01D9/06 ,  F02C7/18 ,  F01D25/32

Abstract: A coolable airfoil has a passage 94 for discharging particulates entrained in cooling air to provide clean cooling air to the leading edge 60 of the airfoil. A chordwise duct 100 extends past a spanwisely extending supply passage 92 to the inlet of a spanwisely extending rear passage 94 such that momentum effects direct the flow of a portion of cooling air and particulates from the duct, past the entrance of the supply passage 92 and into the rear passage 94. The rear passage 94 has a purge hole 96 through which the particulates may be removed.

公开(公告)号：DE69826367T2

公开(公告)日：2005-02-17

申请号：DE69826367

申请日：1998-06-26

Applicant: UNITED TECHNOLOGIES CORP HARTF

Inventor： FUKUDA TAKAO ,  PRICE FRANCIS R ,  COOK CONAN P ,  HOFF RICHARD W ,  SINGER IRWIN D

IPC: F01D9/02 ,  F01D5/18 ,  F01D9/06 ,  F02C7/18 ,  F01D25/32

Abstract: A coolable airfoil has a passage 94 for discharging particulates entrained in cooling air to provide clean cooling air to the leading edge 60 of the airfoil. A chordwise duct 100 extends past a spanwisely extending supply passage 92 to the inlet of a spanwisely extending rear passage 94 such that momentum effects direct the flow of a portion of cooling air and particulates from the duct, past the entrance of the supply passage 92 and into the rear passage 94. The rear passage 94 has a purge hole 96 through which the particulates may be removed.

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。

公开(公告)号：EP3099901A4

公开(公告)日：2017-02-01

申请号：EP14881024

申请日：2014-12-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DOWNEY JAMES B JR ,  ZHANG BRENDA ,  LEMIEUX STEVEN G ,  KAUFMAN ELEANOR D ,  FUKUDA TAKAO ,  NADEAU DANIEL C

IPC: F01D5/18 ,  F02C7/18

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

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.