公开(公告)号：US20150354369A1

公开(公告)日：2015-12-10

申请号：US14728568

申请日：2015-06-02

Applicant: United Technologies Corporation

Inventor： Wieslaw A. Chlus ,  Seth J. Thomen

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/143 ,  F01D5/187 ,  F05D2250/292 ,  F05D2250/312 ,  F05D2250/314 ,  F05D2250/322 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine includes an airfoil that extends from a platform that has first and second circumferential sides that respectively extend to first and second circumferential edges. The first circumferential side has a tapered surface at a first angle relative to a flow path surface. The second circumferential surface has a cooling hole that extends toward the second lateral edge at a second angle relative to the flow path surface. The tapered surface and the cooling hole are axially aligned with one another.

Abstract translation: 用于燃气涡轮发动机的翼型件包括从具有分别延伸到第一和第二圆周边缘的第一和第二圆周侧的平台延伸的翼型件。 第一圆周侧相对于流路表面具有第一角度的锥形表面。 第二圆周表面具有相对于流路表面以第二角度朝向第二侧边缘延伸的冷却孔。 锥形表面和冷却孔彼此轴向对准。

公开(公告)号：US10156150B2

公开(公告)日：2018-12-18

申请号：US14769208

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Wieslaw A. Chlus ,  Seth J. Thomen

IPC: F01D5/22 ,  F01D9/04 ,  F01D9/02

Abstract: An airfoil component for a gas turbine engine includes a platform joined to an airfoil. The platform includes a flow path surface that extends between spaced apart lateral surfaces. The airfoil extends from the flow path surface. A contoured surface adjoins the flow path surface and one of the lateral surfaces.

公开(公告)号：US09850761B2

公开(公告)日：2017-12-26

申请号：US14762582

申请日：2014-01-24

Applicant: United Technologies Corporation

Inventor： Seth J. Thomen ,  Wieslaw A. Chlus

IPC: F01D5/18 ,  F01D5/08 ,  F01D5/02 ,  F02C3/04 ,  F02C7/18

CPC classification number: F01D5/186 ,  F01D5/02 ,  F01D5/081 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2250/23 ,  F05D2250/232 ,  F05D2250/27 ,  F05D2250/711 ,  F05D2260/202 ,  Y02T50/676 ,  Y10T29/49343

Abstract: An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets.