公开(公告)号：EP2852744B1

公开(公告)日：2019-07-17

申请号：EP13793500.3

申请日：2013-05-14

Applicant: United Technologies Corporation

Inventor： VO, Tuan David ,  STENMAN, Christina A. ,  DUELM, Shelton O.

IPC: F02C7/20 ,  F02C7/05 ,  F02K3/00 ,  F01D9/06 ,  F01D5/08 ,  F01D25/24

公开(公告)号：EP2959119B1

公开(公告)日：2018-10-03

申请号：EP14754289.8

申请日：2014-01-28

Applicant: United Technologies Corporation

Inventor： SANDER, David J. ,  DUELM, Shelton O.

IPC: F01D25/24 ,  F02C7/20

CPC classification number: F01D25/26 ,  F01D9/041 ,  F01D25/162 ,  F01D25/246 ,  F02C7/20 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2230/642 ,  F05D2230/644 ,  F05D2240/12 ,  F05D2240/14 ,  Y02T50/672 ,  Y02T50/673

Abstract: An attachment structure for a gas turbine engine includes a frame that has a first annular case. A second annular case extends around the frame. The first annular case and the second annular case include a plurality of interlocks. Each of the interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second case. The first member is received in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.

公开(公告)号：EP2956625B1

公开(公告)日：2017-11-29

申请号：EP14751134.9

申请日：2014-01-29

Applicant: United Technologies Corporation

Inventor： CHANG, Hoyt Y. ,  DUELM, Shelton O.

IPC: F01D5/14 ,  F02C7/00 ,  F01D5/28 ,  F01D5/18 ,  F01D9/02 ,  F01D9/04 ,  F01D25/16

CPC classification number: F01D9/02 ,  F01D5/147 ,  F01D5/18 ,  F01D5/282 ,  F01D5/284 ,  F01D9/041 ,  F01D25/162 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2300/2261 ,  F05D2300/44 ,  F05D2300/6012 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

Abstract: A vane assembly within a mid-turbine frame of a gas turbine engine includes an airfoil that extends between an outer platform and an inner platform. The airfoil includes an outer wall defining a leading edge of a first radius. An inner wall of the airfoil defines an inner cavity including a forward portion proximate the leading edge defining a second radius different than the first radius.

公开(公告)号：EP3049626A1

公开(公告)日：2016-08-03

申请号：EP14846447.2

申请日：2014-09-15

Applicant: United Technologies Corporation

Inventor： DUELM, Shelton O. ,  MCCAFFREY, Michael G.

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/28

CPC classification number: F01D5/282 ,  F01D5/147 ,  F01D5/284 ,  F01D9/041 ,  F05D2240/122 ,  F05D2300/6033

Abstract: An airfoil component includes an insert that has angled faces joined at an edge that provides an airfoil trailing edge. An outer CMC fiber layer overlaps the angled faces to provide a trailing edge portion of an airfoil.

Abstract translation: 机翼部件包括插入件，其具有在提供翼型后缘的边缘处连接的成角度的面。 外部CMC纤维层与成角度的面重叠以提供翼型的后缘部分。

公开(公告)号：EP2959119A1

公开(公告)日：2015-12-30

申请号：EP14754289.8

申请日：2014-01-28

Applicant: United Technologies Corporation

Inventor： SANDER, David J. ,  DUELM, Shelton O.

IPC: F01D25/24 ,  F02C7/20

CPC classification number: F01D25/26 ,  F01D9/041 ,  F01D25/162 ,  F01D25/246 ,  F02C7/20 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2230/642 ,  F05D2230/644 ,  F05D2240/12 ,  F05D2240/14 ,  Y02T50/672 ,  Y02T50/673

Abstract: An attachment structure for a gas turbine engine includes a frame that has a first annular case. A second annular case extends around the frame. The first annular case and the second annular case include a plurality of interlocks. Each of the interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second case. The first member is received in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.

公开(公告)号：EP2900942A2

公开(公告)日：2015-08-05

申请号：EP13860847.6

申请日：2013-09-16

Applicant: United Technologies Corporation

Inventor： VO, Tuan David ,  DUELM, Shelton O.

IPC: F01D25/26 ,  F01D25/24 ,  F02C7/00

CPC classification number: F02C7/24 ,  F01D9/023 ,  F01D25/145 ,  F01D25/26 ,  F02C7/20 ,  F05D2240/14 ,  F05D2240/15 ,  F05D2260/231 ,  Y02T50/675

Abstract: A heat shield for a mid-turbine frame has a conical body, including at least one axial retention feature, at least one circumferential retention feature, and at least one radial retention feature.

Abstract translation: 用于中涡轮机框架的隔热罩具有锥形体，其包括至少一个轴向保持特征，至少一个圆周保持特征和至少一个径向保持特征。