公开(公告)号：EP2938837B1

公开(公告)日：2018-06-27

申请号：EP13868215.8

申请日：2013-12-23

Applicant: United Technologies Corporation

Inventor： CHUONG, Conway ,  BUDNICK, Matthew

IPC: F01D25/16 ,  F01D11/00

CPC classification number: F01D11/001 ,  F01D11/003 ,  F01D11/005 ,  F01D25/162 ,  F01D25/24 ,  F01D25/246 ,  F02C7/28 ,  F05D2240/55

Abstract: A gas turbine engine assembly includes a second module connected axially to a first module along a joint, and an annular cavity defined between the first module and the second module. The seal assembly is disposed proximate the cavity, and includes a seal support ring, a first finger seal, and a second finger seal. The support ring has a backing portion secured to a radial wall of to the first module, and a first seal land extending axially into the cavity away from the first module. The first finger seal has a free end adapted to contact an inner side of the first seal land. The second finger seal is adapted to seal a radially outer portion of the annular cavity.

公开(公告)号：EP3030753A1

公开(公告)日：2016-06-15

申请号：EP14835036.6

申请日：2014-07-18

Applicant: United Technologies Corporation

Inventor： BUDNICK, Matthew ,  CHUONG, Conway

IPC: F01D11/00 ,  F02C7/28

CPC classification number: F01D11/005 ,  F01D11/001 ,  F01D15/10 ,  F01D25/24 ,  F02C7/28 ,  F05D2220/30 ,  F05D2220/76 ,  F05D2240/55

Abstract: A gas turbine engine includes an engine static structure. A fairing is supported relative to the engine static structure and configured to provide a flow path surface of a flow path extending in an axial direction. A seal plate has first and second ends radially spaced from one another with respect to the axial direction. The first end is operatively secured to the engine static structure. The second end is configured to seal relative to the fairing. The seal plate includes a portion between the first and second ends that extends substantially in the axial direction and configured to permit the second end to move away from the fairing in the axial direction relative to the first end in response to thermal growth.

Abstract translation: 燃气涡轮发动机包括发动机静止结构。 整流罩相对于发动机静态结构被支撑，并且构造成提供沿轴向延伸的流动路径的流路表面。 密封板具有相对于轴向方向彼此径向间隔开的第一和第二端。 第一端可操作地固定到发动机静态结构。 第二端被配置为相对于整流罩密封。 密封板包括在第一和第二端之间的基本上在轴向方向上延伸的部分，并且构造成允许第二端响应于热增长而相对于第一端沿轴向方向远离整流罩移动。

公开(公告)号：EP2938834A1

公开(公告)日：2015-11-04

申请号：EP13869778.4

申请日：2013-01-23

Applicant: United Technologies Corporation

Inventor： BUDNICK, Matthew

IPC: F01D11/00

CPC classification number: F01D11/003 ,  F01D11/005 ,  F01D25/30

Abstract: A turbine seal system comprises a structural frame, a structural member, a seal and a bumper. The structural member is disposed opposite the structural frame. The seal extends between the structural frame and the structural member. The bumper is anchored to the structural frame or the structural member and extends toward a mid-region of the seal. In one embodiment, the structural frame comprises a ring-strut-ring turbine exhaust case.

公开(公告)号：EP3030753B1

公开(公告)日：2018-12-26

申请号：EP14835036.6

申请日：2014-07-18

Applicant: United Technologies Corporation

Inventor： BUDNICK, Matthew ,  CHUONG, Conway

IPC: F01D11/00 ,  F02C7/28 ,  F01D15/10 ,  F01D25/24

CPC classification number: F01D11/005 ,  F01D11/001 ,  F01D15/10 ,  F01D25/24 ,  F02C7/28 ,  F05D2220/30 ,  F05D2220/76 ,  F05D2240/55

Abstract: A gas turbine engine includes an engine static structure. A fairing is supported relative to the engine static structure and configured to provide a flow path surface of a flow path extending in an axial direction. A seal plate has first and second ends radially spaced from one another with respect to the axial direction. The first end is operatively secured to the engine static structure. The second end is configured to seal relative to the fairing. The seal plate includes a portion between the first and second ends that extends substantially in the axial direction and configured to permit the second end to move away from the fairing in the axial direction relative to the first end in response to thermal growth.

公开(公告)号：EP2938833B1

公开(公告)日：2017-11-01

申请号：EP13876268.7

申请日：2013-12-16

Applicant: United Technologies Corporation

Inventor： CHUONG, Conway ,  SCOTT, Jonathan Ariel ,  BUDNICK, Matthew

IPC: F01D9/04 ,  F01D25/28 ,  F02C7/00 ,  F01D25/16 ,  F02C7/20

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

公开(公告)号：EP2938838B1

公开(公告)日：2017-07-05

申请号：EP13868633.2

申请日：2013-12-17

Applicant: United Technologies Corporation

Inventor： CHUONG, Conway ,  BUDNICK, Matthew

IPC: F01D11/02 ,  F01D5/20 ,  F01D11/00 ,  F01D25/28 ,  F01D25/30 ,  F02C7/28

CPC classification number: F02C7/28 ,  F01D11/005 ,  F01D25/28 ,  F01D25/30

公开(公告)号：EP2938842A2

公开(公告)日：2015-11-04

申请号：EP13876419.6

申请日：2013-12-16

Applicant: United Technologies Corporation

Inventor： CHUONG, Conway ,  BUDNICK, Matthew

IPC: F01D25/12 ,  F01D9/04 ,  F01D25/28 ,  F02C7/12 ,  F02C7/20

CPC classification number: F01D25/246 ,  F01D25/162 ,  F05D2260/201 ,  Y02T50/675

Abstract: An assembly includes a gas turbine engine component and a plate. The plate is spaced from a surface of the component and generally conforms to the shape of the surface. The plate and component form a passageway that allows for passage of a secondary gas flow between the component and the plate.

公开(公告)号：EP2938833A2

公开(公告)日：2015-11-04

申请号：EP13876268.7

申请日：2013-12-16

Applicant: United Technologies Corporation

Inventor： CHUONG, Conway ,  SCOTT, Jonathan Ariel ,  BUDNICK, Matthew

IPC: F01D9/04 ,  F01D25/28 ,  F02C7/00

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，安装件和整流罩。 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：EP2938841B1

公开(公告)日：2017-06-28

申请号：EP13869347.8

申请日：2013-12-16

Applicant: United Technologies Corporation

Inventor： CHUONG, Conway ,  BUDNICK, Matthew

IPC: F01D25/12 ,  F02C7/12

CPC classification number: F02C7/20 ,  F01D11/14 ,  F01D25/12 ,  F01D25/162 ,  F01D25/243 ,  F01D25/265 ,  F01D25/28 ,  Y02T50/675

公开(公告)号：EP2938844B1

公开(公告)日：2017-02-08

申请号：EP13866906.4

申请日：2013-12-18

Applicant: United Technologies Corporation

Inventor： YEAGER, William ,  CHUONG, Conway ,  BUDNICK, Matthew

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

CPC classification number: F01D25/14 ,  F01D9/041 ,  F01D9/065 ,  F01D25/162 ,  F01D25/30 ,  F02C7/18 ,  F05D2240/15 ,  Y02T50/675

Abstract: A turbine exhaust case employed in an industrial gas turbine engine includes a frame, a fairing and a heat shield. The frame includes an outer ring, an inner ring, and struts connected between the outer ring and the inner ring. The fairing includes a fairing outer ring, a fairing inner ring, and fairing struts connected between the fairing outer ring and the fairing inner ring. The heat shield is located between the frame outer ring and the fairing outer ring and provides a thermal barrier between the fairing outer ring and the frame outer ring, wherein the heat shield includes an aft portion having a flange that interfaces with the frame outer ring to form an air dam that directs cooling airflow forward along the frame outer ring within an outer diameter cavity formed between the frame outer ring and the heat shield.

Abstract translation: 在工业燃气涡轮发动机中使用的涡轮机排气箱包括框架，整流罩和隔热罩。 框架包括外圈，内圈和连接在外环和内圈之间的支柱。 整流罩包括整流罩外圈，整流罩内圈和整流罩外圈和整流罩内圈之间的整流罩支柱。 隔热罩位于框架外圈和整流罩外圈之间，并且在整流罩外圈和框架外圈之间提供热障，其中隔热罩包括具有与框架外环相接合的凸缘的后部， 形成一个空气坝，其在框架外环和隔热罩之间形成的外径腔内沿着框架外圈向前引导冷却气流。