公开(公告)号：JPH11141353A

公开(公告)日：1999-05-25

申请号：JP26000098

申请日：1998-09-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BOURSY ANDREW P

IPC: F01D25/12 ,  F01D25/00 ,  F02C7/12 ,  F02C7/30

Abstract: PROBLEM TO BE SOLVED: To protect a high pressure turbine case in a gas turbine engine from the corrosion action of the particulate matter in the cooling air current. SOLUTION: An array of first stator vanes 34 is fixed to a turbine case 30 by a first vane support part 40. A cap-shaped corrosive energy dispersing device 44 having a pair of intake orifices 46 opposite to each other and an exhaust orifice having a large diameter, is provided on a bore of the vane support part 40. The air currents including the particulate matter are collided with each other, and the energy is reduced and further decelerated to be discharged, whereby the corrosion can be inhibited.

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：DE69827887T2

公开(公告)日：2005-04-07

申请号：DE69827887

申请日：1998-09-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BOURSY ANDREW P

IPC: F01D25/12 ,  F01D25/00 ,  F02C7/12 ,  F02C7/30 ,  F01D5/28

Abstract: A turbine 18 of a gas turbine engine includes erosion energy dissipaters 44 which reduce the erosion of associated structure due to impingement of particulates entrained in airstreams, particularly cooling airstreams. Each dissipater comprises a plurality of inlet orifices 46 and a large diameter outlet orifice 48. The inlet orifices 46 are arranged to produce impacting gas streams which reduces the energy of the particulates, and the outlet orifice 48 lowers the velocity of the resultant gas stream thereby reducing erosion damage.

公开(公告)号：DE69827887D1

公开(公告)日：2005-01-05

申请号：DE69827887

申请日：1998-09-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BOURSY ANDREW P

IPC: F01D25/12 ,  F01D25/00 ,  F02C7/12 ,  F02C7/30 ,  F01D5/28

Abstract: A turbine 18 of a gas turbine engine includes erosion energy dissipaters 44 which reduce the erosion of associated structure due to impingement of particulates entrained in airstreams, particularly cooling airstreams. Each dissipater comprises a plurality of inlet orifices 46 and a large diameter outlet orifice 48. The inlet orifices 46 are arranged to produce impacting gas streams which reduces the energy of the particulates, and the outlet orifice 48 lowers the velocity of the resultant gas stream thereby reducing erosion damage.

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。