公开(公告)号：WO2014143317A3

公开(公告)日：2014-12-24

申请号：PCT/US2013076758

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BUDNICK MATTHEW ,  CHUONG CONWAY ,  SCOTT JONATHAN A

IPC: F01D11/00 ,  F01D9/04 ,  F02C7/28

CPC classification number: F01D11/005 ,  F01D25/162 ,  F01D25/246

Abstract: A turbine seal system comprises an annular structural frame, a circumferential ring, a fairing and a seal. The circumferential ring is joined to the annular structural frame. The fairing is disposed within the annular structural frame and is engaged with the circumferential ring to limit circumferential rotation of the fairing with respect to the annular structural frame. The seal extends between the fairing and the circumferential ring. In one embodiment, the structural component comprises a ring-strut-ring turbine exhaust case.

Abstract translation: 涡轮机密封系统包括环形结构框架，周向环，整流罩和密封件。 周向环连接到环形结构框架。 整流装置设置在环形结构框架内并且与周向环接合以限制整流装置相对于环形结构框架的周向旋转。 密封件在整流罩和圆周环之间延伸。 在一个实施例中，结构部件包括环形支撑环涡轮排气箱。

公开(公告)号：WO2014133647A2

公开(公告)日：2014-09-04

申请号：PCT/US2013075368

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHUONG CONWAY ,  SCOTT JONATHAN A ,  BUDNICK MATTHEW

CPC classification number: F02C7/20 ,  F01D25/162 ,  F01D25/28 ,  F05D2250/42

Abstract: An assembly for a gas turbine engine includes a frame, a mount, and a fairing. The mount is attached to the frame and the fairing is connected to the mount. The fairing and mount have mating anti-deflection features that engage to prevent circumferential movement of the fairing relative to the frame.

Abstract translation: 用于燃气涡轮发动机的组件包括框架，底座和整流罩。 安装架连接到框架，整流罩连接到安装座。 整流罩和安装座具有接合防偏转特征，其接合以防止整流罩相对于框架的圆周运动。

公开(公告)号：EP2938845A4

公开(公告)日：2016-01-13

申请号：EP13868402

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCOTT JONATHAN A ,  VENINGER ALBERT

IPC: F01D9/04 ,  F01D25/14 ,  F01D25/30

CPC classification number: F01D25/145 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D25/005 ,  F01D25/12 ,  F01D25/125 ,  F01D25/162 ,  F01D25/24 ,  F01D25/30 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/231 ,  Y02T50/673 ,  Y02T50/675

Abstract: A turbine exhaust case (28) for a gas turbine engine (10) comprises a frame (100), a vane fairing (108), a heat shield (124, 126, 128), and a serpentine cooling path. The frame has an outer ring (102) and an inner ring (104) connected by a hollow strut (106) with a radial service line passage (132). The vane fairing is disposed between the inner ring and the outer ring to define a core airflow path. The heat shield is disposed between the vane fairing and the frame. The serpentine cooling flow path passes through and around the outer ring, the inner ring, and the plurality of struts

公开(公告)号：EP2938863A4

公开(公告)日：2016-08-31

申请号：EP13868006

申请日：2013-12-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BUDNICK MATTHEW ,  CHUONG CONWAY ,  SCOTT JONATHAN A

IPC: F01D25/16 ,  F01D9/04 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D25/145 ,  F01D25/162 ,  F01D25/24 ,  F01D25/246 ,  F01D25/28 ,  F01D25/30 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2260/231 ,  F05D2260/30 ,  F05D2260/31