公开(公告)号：WO2014160215A1

公开(公告)日：2014-10-02

申请号：PCT/US2014/026062

申请日：2014-03-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： HOUGH, Matthew A. ,  BEATTIE, Jeffrey S.

IPC: F01D5/22 ,  F01D5/30 ,  F02C7/20

CPC classification number: F01D5/141 ,  F01D5/147 ,  F01D5/22 ,  F01D5/3007 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2240/80 ,  F05D2250/14 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/941

Abstract: A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.

Abstract translation: 用于涡轮发动机的转子叶片包括连接到基座的翼型件。 底座包括平台，颈部和圆角。 圆角沿平台和颈部之间的交叉点的至少一部分延伸。 圆角的半径随着圆角从平台延伸到颈部而基本上连续变化。

公开(公告)号：EP2971553B1

公开(公告)日：2019-11-13

申请号：EP14773918.9

申请日：2014-03-13

Applicant: United Technologies Corporation

Inventor： HOUGH, Matthew A. ,  BEATTIE, Jeffrey S.

IPC: F01D5/22 ,  F01D5/30 ,  F02C7/20 ,  F01D5/14

公开(公告)号：EP3670840A1

公开(公告)日：2020-06-24

申请号：EP19204409.7

申请日：2019-10-21

Applicant: United Technologies Corporation

Inventor： HOUGH, Matthew A. ,  HANSON, Russell B. ,  TU, John S. ,  CROTEAU, Paul F. ,  SANCHEZ, Paul K. ,  HARMON, Stephen C. ,  RATHGEB, Joshua C.

IPC: F01D9/02 ,  F01D9/06 ,  F01D25/12 ,  F01D25/16 ,  F01D25/26

Abstract: A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing (48) disposed circumferentially about a longitudinal axis (24). The fairing forms at least a portion of a fluid path (C) between a compressor (40) and a combustor (44) of the gas turbine engine (10). The fairing (48) defines a plurality of apertures (50) extending through the fairing (48). At least one spoke (50) extends through at least one respective aperture (50) of the plurality of apertures (50). The at least one spoke (58) is configured to couple an inner diffuser case (54) and an outer diffuser case (56) of the gas turbine engine (10).

公开(公告)号：EP2971553A1

公开(公告)日：2016-01-20

申请号：EP14773918.9

申请日：2014-03-13

Applicant: United Technologies Corporation

Inventor： HOUGH, Matthew A. ,  BEATTIE, Jeffrey S.

IPC: F01D5/22 ,  F01D5/30 ,  F02C7/20

Abstract: A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.