公开(公告)号：WO2014058493A3

公开(公告)日：2014-06-19

申请号：PCT/US2013050429

申请日：2013-07-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHLUS WIESLAW A ,  THOMEN SETH J

IPC: F01D5/18 ,  F02C7/12

CPC classification number: F01D5/20 ,  F05D2250/14 ,  F05D2250/232 ,  F05D2250/324 ,  F05D2260/202 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.

Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供在径向方向上延伸的翼型件。 翼型件具有设置在压力和吸力壁之间的冷却通道，其朝向翼型件的尖端延伸。 尖端包括分隔压力和吸力壁的口袋。 围绕的冷却孔将冷却通道流体地连接到口袋。 所述被切割的冷却孔包括凹入到所述吸入壁的表面并暴露于所述口袋的部分。

公开(公告)号：EP2971674A4

公开(公告)日：2016-11-02

申请号：EP14775158

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHLUS WIESLAW A ,  THOMEN SETH J

IPC: F01D9/04

CPC classification number: F01D9/042 ,  F01D9/023 ,  F01D9/041 ,  F05D2240/81 ,  Y02T50/672 ,  Y02T50/676

公开(公告)号：EP2895697A4

公开(公告)日：2015-12-02

申请号：EP13837103

申请日：2013-09-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THOMEN SETH J ,  PIETRASZKIEWICZ EDWARD F

IPC: F01D5/14 ,  F01D5/00 ,  F01D5/30 ,  F02C7/00 ,  F02K3/00

CPC classification number: F01D5/147 ,  F01D5/3007 ,  F05D2240/80

公开(公告)号：EP3036405A4

公开(公告)日：2017-05-10

申请号：EP14837927

申请日：2014-08-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THOMEN SETH J ,  PIETRASZKIEWICZ EDWARD F

IPC: F01D5/18 ,  F01D9/04 ,  F01D9/06 ,  F01D11/08 ,  F01D11/24 ,  F01D25/12 ,  F02C7/12 ,  F02C7/18 ,  F04D29/54 ,  F04D29/58

CPC classification number: F01D25/12 ,  F01D9/041 ,  F01D9/065 ,  F01D11/08 ,  F01D11/24 ,  F02C7/12 ,  F04D29/164 ,  F04D29/542 ,  F04D29/582 ,  F04D29/584 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/11 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141

公开(公告)号：EP2885504A4

公开(公告)日：2015-08-26

申请号：EP13846039

申请日：2013-07-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHLUS WIESLAW A ,  THOMEN SETH J

IPC: F01D5/20

CPC classification number: F01D5/20 ,  F05D2250/14 ,  F05D2250/232 ,  F05D2250/324 ,  F05D2260/202 ,  Y02T50/676

公开(公告)号：EP3030750A4

公开(公告)日：2017-04-26

申请号：EP14834675

申请日：2014-07-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHLUS WIESLAW A ,  THOMEN SETH J

IPC: F01D5/18 ,  F02C7/12 ,  F04D29/58

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D5/20 ,  F02C7/18 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2250/324 ,  F05D2260/202

公开(公告)号：EP2935793A4

公开(公告)日：2016-03-23

申请号：EP13863951

申请日：2013-11-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THOMEN SETH J ,  CHLUS WIESLAW A

IPC: F01D5/30 ,  F01D11/00 ,  F01D11/08

CPC classification number: F01D11/006 ,  F01D5/3007 ,  F01D5/3092 ,  F05D2300/173

Abstract: A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil.