公开(公告)号：US20200095893A1

公开(公告)日：2020-03-26

申请号：US16142515

申请日：2018-09-26

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark ,  Daniel J. Whitney

IPC: F01D25/24 ,  F01D11/08 ,  F01D25/00

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one rotor and at least one blade extending radially outwardly from the rotor to a radially outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip of the blade. The blade outer air seal has forward and aft hooks. The forward and aft hooks support the blade outer air seal. The blade outer air seal is formed with a central web. The forward and aft hooks extending from the central web at a T-joint. There is a pair of mating inner laminate at the T-joint each having an axially extending portion and a vertically extending portion. The pair of mating inner laminates have an interwoven connection. A method is also disclosed.

公开(公告)号：US20200072127A1

公开(公告)日：2020-03-05

申请号：US16122431

申请日：2018-09-05

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: F02C7/18 ,  F02C3/04 ,  F02C9/16

Abstract: A turbine section for a gas turbine engine includes a turbine blade that extends radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is mounted in a support structure and is arranged radially outward of the outer tip. A flow guide is arranged between the support structure and the blade outer air seal and defines a passage between the flow guide and the blade outer air seal. The passage is configured to communicate air in a generally axial direction.

公开(公告)号：US20200072071A1

公开(公告)日：2020-03-05

申请号：US16122553

申请日：2018-09-05

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Paul M. Lutjen ,  Thomas E. Clark

IPC: F01D11/08

Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The blade outer air seal has a lip at an axial end engaged with the support structure. A seal structure has a seal portion and a wear liner portion joined by a radially extending portion. The seal portion is radially outward of the lip and the wear liner is radially inward of the lip.

公开(公告)号：US20200072067A1

公开(公告)日：2020-03-05

申请号：US16122525

申请日：2018-09-05

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: F01D11/00 ,  F01D25/24 ,  F01D11/08

Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. A flow guide has a plurality of flow guide segments arranged between the blade outer air seal and the support structure. An intersegment seal is at a circumferential end of at least one of the flow guide segments.

公开(公告)号：US20200025029A1

公开(公告)日：2020-01-23

申请号：US16042096

申请日：2018-07-23

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: F01D25/14 ,  F01D25/12 ,  F01D11/12

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a chamber within the attachment block, and communicates to circumferential edges of the attachment block to direct cooling air along the central web of the blade outer air seal. A blade outer air seal assembly is also disclosed.

公开(公告)号：US20200003077A1

公开(公告)日：2020-01-02

申请号：US16019972

申请日：2018-06-27

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Ken F. Blaney

IPC: F01D25/28 ,  F01D11/08

Abstract: An attachment body for a blade outer air seal includes a leading edge connected to a trialing edge by a radially inner wall and a radially outer wall. At least one forward hook extends from the radially outer wall. At least one aft hook extends from the radially outer wall. At least one post extends from the radially outer surface and has a blade outer air seal (BOAS) guide surface.

公开(公告)号：US10247028B2

公开(公告)日：2019-04-02

申请号：US15025602

申请日：2014-08-05

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Paul M. Lutjen

IPC: F01D11/08 ,  F01D11/18 ,  F16J15/44

Abstract: A clearance control system for a gas turbine engine is provided. The system includes an inner axial wall that extends between a forward wall and an aft wall. The system also includes an outer axial wall that extends parallel to the inner axial wall to pivotally receive a full hoop thermal control ring.

公开(公告)号：US20170211415A1

公开(公告)日：2017-07-27

申请号：US15005061

申请日：2016-01-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anthony B Swift ,  Ken F. Blaney ,  Paul M. Lutjen ,  Neil L. Tatman ,  Dominic J. Mongillo

IPC: F01D25/12 ,  F01D9/04 ,  F01D5/14 ,  F02C7/12 ,  F01D11/08

Abstract: A gas turbine engine component has a body extending between two circumferential sides, and between a leading edge and a trailing edge. A refractory metal core within the body forms at least one cooling circuit to utilize fluid to cool the body. When the refractory metal core is removed from the body, the at least one cooling circuit includes an inlet, an outlet, and a passage that varies in cross-sectional area between the inlet and outlet. A method of manufacturing a gas turbine engine, a method of manufacturing a core, and a refractory metal core are also disclosed.

公开(公告)号：US20170198599A1

公开(公告)日：2017-07-13

申请号：US14994208

申请日：2016-01-13

Applicant: United Technologies Corporation

Inventor： Kevin J. Ryan ,  Terence P. Tyler, JR. ,  Ken F. Blaney

IPC: F01D11/08 ,  F02C7/18 ,  F01D25/12 ,  F02C3/04

CPC classification number: F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.

公开(公告)号：US20160237842A1

公开(公告)日：2016-08-18

申请号：US15025602

申请日：2014-08-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ken F. Blaney ,  Paul M. Lutjen

IPC: F01D11/18 ,  F16J15/44

CPC classification number: F01D11/18 ,  F01D11/08 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/55 ,  F05D2240/91 ,  F05D2260/30 ,  F05D2300/5021 ,  F16J15/445 ,  Y02T50/672

Abstract: A clearance control system for a gas turbine engine is provided. The system includes an inner axial wall that extends between a forward wall and an aft wall. The system also includes an outer axial wall that extends parallel to the inner axial wall to pivotally receive a full hoop thermal control ring.

Abstract translation: 提供了一种用于燃气涡轮发动机的间隙控制系统。 该系统包括在前壁和后壁之间延伸的内轴向壁。 该系统还包括外轴向壁，其平行于内轴向壁延伸以枢转地接收全环热控制环。