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：WO2015084450A3

公开(公告)日：2015-08-27

申请号：PCT/US2014055439

申请日：2014-09-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHANG HOYT Y ,  ICHIHASHI YUSUKE ,  FUJIMOTO YOHEI ,  DALE TIMOTHY

IPC: F02C7/00 ,  F02C7/20 ,  F23M5/00

CPC classification number: F02C7/28 ,  F01D11/005 ,  F01D25/30 ,  F02K1/805 ,  F02K1/82 ,  F02K1/825 ,  F05D2220/32 ,  F05D2220/90 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2250/12 ,  F05D2250/14 ,  F16J15/021 ,  F16J15/06 ,  Y02T50/671

Abstract: A case is provided for a gas turbine engine. The case includes a wall defining a through-hole. The case also includes first and second pockets adjacent to, and on opposite sides, of the through hole. A method of reducing stress in a case of a gas turbine engine is also provided that includes reducing stress about a through-hole by providing a concavity on each side of the through-hole.

Abstract translation: 为燃气涡轮发动机提供了一种情况。 壳体包括限定通孔的壁。 壳体还包括与通孔相邻并在相对侧上的第一和第二凹穴。 还提供了一种在燃气涡轮发动机的情况下减小应力的方法，其包括通过在通孔的每一侧上提供凹面来减小关于通孔的应力。

公开(公告)号：WO2014074195A3

公开(公告)日：2014-08-21

申请号：PCT/US2013055490

申请日：2013-08-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HARRIS MEGGAN ,  FARAH JORGE I ,  TREAT CHRISTOPHER ,  DALE TIMOTHY

IPC: F01D25/24 ,  F02C7/00

CPC classification number: F01D25/28 ,  F01D25/162 ,  F16B9/023 ,  Y10T29/49323

Abstract: A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.

Abstract translation: 涡轮发动机包括多个层架支架。 每个层架支撑件通过多个紧固件和至少一个自反向旋转衬套部件连接到涡轮发动机的内框架壳体。

公开(公告)号：EP2888454A4

公开(公告)日：2016-04-20

申请号：EP13853570

申请日：2013-08-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HARRIS MEGGAN ,  FARAH JORGE I ,  TREAT CHRISTOPHER ,  DALE TIMOTHY

IPC: F01D25/24 ,  F01D25/16 ,  F01D25/28 ,  F02C7/00 ,  F16B9/02

CPC classification number: F01D25/28 ,  F01D25/162 ,  F16B9/023 ,  Y10T29/49323

Abstract: A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.

公开(公告)号：EP3066318A4

公开(公告)日：2016-09-14

申请号：EP14857096

申请日：2014-10-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DALE TIMOTHY ,  BHANDERI SWATI G

IPC: F02C7/00 ,  F01D25/24 ,  F01D25/30 ,  F23R3/42

CPC classification number: F01D9/02 ,  F01D25/24 ,  F01D25/243 ,  F01D25/246 ,  F01D25/30 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/941 ,  F23R3/04 ,  F23R3/10 ,  F23R3/50 ,  Y02T50/675

公开(公告)号：EP3044441A4

公开(公告)日：2016-11-30

申请号：EP14844779

申请日：2014-09-12

Applicant: UNITED TECHNOLOGIES CORP ,  MITSUBISHI HEAVY IND AMERICA INC

Inventor： CHANG HOYT Y ,  ICHIHASHI YUSUKE ,  FUJIMOTO YOHEI ,  DALE TIMOTHY

IPC: F02C7/20 ,  F01D25/08 ,  F01D25/24 ,  F02C7/24 ,  F23R3/00 ,  F23R3/06

CPC classification number: F01D25/24 ,  F05D2250/20 ,  F05D2250/712 ,  F05D2250/713 ,  F23R3/002 ,  F23R2900/00005 ,  Y02T50/671

公开(公告)号：EP2971692A4

公开(公告)日：2016-11-16

申请号：EP13878455

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HYLAND DAVE J ,  CAPRARIO JOSEPH T ,  DALE TIMOTHY

IPC: F02C7/28 ,  F01D11/00 ,  F01D11/02 ,  F01D19/00 ,  F01D25/04 ,  F01D25/22 ,  F16J15/44

CPC classification number: F02C7/28 ,  F01D11/001 ,  F01D11/025 ,  F01D19/00 ,  F01D25/04 ,  F01D25/22 ,  F05D2240/53 ,  F05D2260/85 ,  F05D2260/96 ,  F16J15/44 ,  F16J15/442

Abstract: A hydrostatic seal and vibration damping apparatus for a gas turbine engine adapted to reduce vibrations during cold engine start-ups is disclosed. In one disclosed configuration, the vibration damping apparatus is comprised of a temperature sensitive control ring having a relatively high coefficient of thermal expansion adapted to expand quickly at relatively low temperatures to protect the hydrostatic seal during such gas turbine engine startups. At operational temperatures, the control ring is adapted to become separated from the hydrostatic sea.

Abstract translation: 公开了一种用于在冷发动机起动期间减少振动的用于燃气涡轮发动机的液压密封和减振装置。 在一个公开的结构中，减振装置包括温度敏感的控制环，该温度敏感控制环具有相对较高的热膨胀系数，适于在较低温度下快速膨胀以在这种燃气涡轮发动机起动期间保护静水密封。 在操作温度下，控制环适于与静水压海相分离。

公开(公告)号：EP2834502A4

公开(公告)日：2016-03-09

申请号：EP13836824

申请日：2013-03-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DALE TIMOTHY

IPC: F02C7/28 ,  F01D11/00 ,  F01D11/02 ,  F16J15/44

CPC classification number: F16J15/445 ,  F01D11/001 ,  F01D11/02 ,  F01D11/025 ,  F01D11/12 ,  F04D29/083 ,  F05D2240/55 ,  F05D2260/38 ,  F16J15/442