公开(公告)号：JP2013104426A

公开(公告)日：2013-05-30

申请号：JP2012202594

申请日：2012-09-14

Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

Inventor： DAMGAARD JOCELYN C ,  ROBERTS STEVEN D ,  DALE TIMOTHY

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

CPC classification number: F02C7/28 ,  F02K1/805 ,  F05D2250/611

Abstract: PROBLEM TO BE SOLVED: To provide a flexible seal system for a gas turbine engine.SOLUTION: The flexible seal system 16 for the gas turbine engine 10 includes: annular mounting brackets 92, 94; annular support brackets 96, 98, an annular flexible seal 40; and a plurality of mounting spacers 100, 102. The flexible seal 40 extends axially between a first mounting segment 56 and a second mounting segment 58. The first mounting segment 56 is connected axially between the mounting bracket and the support bracket, and includes a plurality of mounting apertures 68 that extend axially through the first mounting segment 56. Each of the mounting spacers 100, 102 is arranged within a respective one of the mounting apertures, and extends axially between the mounting bracket and the support bracket. The first mounting segment is compressed between the mounting bracket and the support bracket.

Abstract translation: 要解决的问题：提供一种用于燃气涡轮发动机的柔性密封系统。 解决方案：用于燃气涡轮发动机10的柔性密封系统16包括：环形安装支架92,94; 环形支撑支架96,98，环形柔性密封件40; 和多个安装间隔件100,102。柔性密封件40在第一安装段56和第二安装段58之间轴向延伸。第一安装段56轴向地连接在安装支架和支撑托架之间，并且包括多个 安装孔68通过第一安装段56轴向延伸。每个安装间隔件100,102布置在相应的一个安装孔内，并且在安装支架和支撑托架之间轴向延伸。 第一安装段在安装支架和支架之间被压缩。 版权所有（C）2013，JPO＆INPIT

公开(公告)号：EP2938826A4

公开(公告)日：2016-02-17

申请号：EP13868447

申请日：2013-10-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HUDON DAVID J ,  ROBERTS STEVEN D ,  SCHIRTZINGER GARY A ,  OTT JOE

IPC: F01D5/12 ,  F01D5/00 ,  F01D17/02 ,  F01D17/08 ,  F02C7/00 ,  G01K1/16

CPC classification number: F01D21/003 ,  F01D17/02 ,  F01D17/08 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2260/83 ,  Y10T29/49

公开(公告)号：EP2943657A4

公开(公告)日：2016-04-06

申请号：EP14737797

申请日：2014-01-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROBERTS STEVEN D ,  TOSI KENNETH F ,  HOGATE ISAAC J ,  SALISBURY GEORGE

IPC: F01D9/02 ,  F01D5/28 ,  F01D25/02 ,  F02C7/00

CPC classification number: F01D9/04 ,  F01D5/147 ,  F01D5/282 ,  F01D9/042 ,  F01D17/10 ,  F01D25/02 ,  F01D25/10 ,  F01D25/246 ,  F05D2220/30 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/437 ,  F05D2300/48

Abstract: An assembly for a turbine engine includes an inner platform, and outer platform and a plurality of structural inlet guide vanes. The outer platform circumscribes the inner platform. The structural inlet guide vanes are arranged around an axis, and extend radially between and are connected to the inner platform and the outer platform. A first of the structural inlet guide vanes includes a structural vane body that is configured from or otherwise includes an organic matrix composite.

Abstract translation: 用于涡轮发动机的组件包括内平台和外平台以及多个结构入口导向叶片。 外部平台围绕内部平台。 结构进口导向叶片围绕轴线布置，并且在内平台和外平台之间径向延伸并连接到内平台和外平台。 结构进口导叶中的第一个包括由有机基质复合材料构成或包括有机基质复合材料的结构叶片体。