公开(公告)号：EP2956646A4

公开(公告)日：2016-10-12

申请号：EP14752111

申请日：2014-02-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPANGLER BRANDON W ,  MONGILLO DOMINIC J

IPC: F01D5/18 ,  F01D5/28 ,  F01D9/06

CPC classification number: F01D9/023 ,  F01D5/186 ,  F01D5/288 ,  F01D9/065 ,  F01D11/20 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/12 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括具有内表面和外表皮的壁，冷却孔，其具有从内表面延伸并且汇合到计量部分 ，以及在计量部分下游延伸到位于外皮的出口的扩散部分。 冷却孔的扩散部分包括在扩散部分的下游表面处的第一侧扩散角，第二侧扩散角和下游扩散角，下游扩散角小于第一侧扩散角和第二侧扩散 角度。

公开(公告)号：EP3039248A4

公开(公告)日：2016-09-14

申请号：EP14840259

申请日：2014-06-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HAGAN BENJAMIN F ,  WAITE RYAN A ,  SPANGLER BRANDON W ,  GAUTSCHI STEVEN B

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

CPC classification number: F01D9/065 ,  F01D5/189 ,  F05D2220/32 ,  F05D2240/126 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2260/204 ,  Y02T50/673 ,  Y02T50/676

Abstract: A vane structure includes an airfoil section with a first inner airfoil wall surface and a second inner airfoil wall surface. A baffle is mounted within the airfoil section between the first inner airfoil wall surface and the second inner airfoil wall surface.

Abstract translation: 叶片结构包括具有第一内翼面壁表面和第二内翼面壁表面的翼型段。 挡板安装在第一内翼面壁表面和第二内翼面壁表面之间的翼型部分内。

公开(公告)号：EP2900961A4

公开(公告)日：2016-07-27

申请号：EP13840873

申请日：2013-09-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SPANGLER BRANDON W ,  ZELESKY MARK F ,  OTERO EDWIN

IPC: F02C7/12 ,  F01D5/18 ,  F02K3/00

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘，后缘，压力侧壁和吸力侧壁之间延伸的翼型件。 冷却回路设置在翼型的内部。 冷却回路包括在翼型件内径向延伸的第一芯腔。 第一轴向皮肤芯在第一轴向皮肤芯的第一位置处与第一芯腔流体连通，并且第二芯腔在第一轴向皮肤芯的第二位置处与第一轴向皮肤皮肤流体连通。

公开(公告)号：EP2828514A4

公开(公告)日：2015-11-11

申请号：EP13764958

申请日：2013-03-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZESS GARY A ,  SPANGLER BRANDON W ,  MONGILLO DOMINIC J

IPC: F02K3/00 ,  F01D5/18 ,  F01D25/08 ,  F02C7/14

CPC classification number: F01D5/187 ,  F05D2240/304 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49337

Abstract: An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, a cooling passageway, and a plurality of oblong pedestals. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge, as well as radially from a root section to a tip section of the airfoil. The cooling passageway is located between the suction surface and the pressure surface. The oblong pedestals connect the suction surface to the pressure surface at the trailing edge of the airfoil.

公开(公告)号：EP2867472A4

公开(公告)日：2015-08-05

申请号：EP13833314

申请日：2013-06-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BERGMAN RUSSELL J ,  BACH LEONARD A ,  SPANGLER BRANDON W

IPC: F01D5/14 ,  F01D5/18 ,  F02C7/00

CPC classification number: F01D9/02 ,  B22C9/04 ,  B22C9/10 ,  F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/2214 ,  Y02T50/672 ,  Y02T50/676

Abstract: A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.