公开(公告)号：US10920600B2

公开(公告)日：2021-02-16

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：US10907492B2

公开(公告)日：2021-02-02

申请号：US16124480

申请日：2018-09-07

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  William M. Barker

IPC: F01D11/08 ,  F01D25/24

Abstract: A gas turbine engine includes a turbine blade rotating about an axis of rotation defining an axial direction. A blade outer air seal is positioned radially outward of a radially outer tip of the turbine blade. The blade outer air seal has a forward support and an aft support. The forward support is supported on a forward hook from a blade outer air seal support. The aft support is supported on an aft hook from the blade outer air seal support. The blade outer air seal has a central web extending between the forward support and the aft support and radially outwardly of the turbine blade radially outer tip. A radially outer chamber is defined radially outwardly of the central web, and axially intermediate the forward support and the aft support. The radially outer chamber is divided into at least two separate subchambers maintained at two different pressures. A forward subchamber is at a higher pressure than an aft subchamber. A seal separator separates the forward and aft subchambers.

公开(公告)号：US10822985B2

公开(公告)日：2020-11-03

申请号：US16116140

申请日：2018-08-29

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Winston Gregory Smiddy ,  Daniel J. Whitney ,  William M. Barker

IPC: F01D11/08

Abstract: A method of forming a gas turbine engine component includes the steps of (a) forming an intermediate portion, (b) forming cooling circuit structure into at least an outer layer of the intermediate portion, (c) providing an outer layer over the formed cooling circuits to close off the cooling circuits, such that there are laminate on both a radially inner and a radially outer side of the cooling circuits, and (d) forming an inlet and an outlet to the cooling circuits through the outer layer. A gas turbine engine is also disclosed.

公开(公告)号：US10808564B2

公开(公告)日：2020-10-20

申请号：US16356144

申请日：2019-03-18

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark

IPC: F01D11/08

Abstract: A blade outer air seal assembly includes a seal segment that has a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first wall is axially spaced from a second wall. The first and second walls extend from the base portion to an outer wall to define a circumferentially extending seal passage. A wear liner is within the seal passage.

公开(公告)号：US20200300109A1

公开(公告)日：2020-09-24

申请号：US16356144

申请日：2019-03-18

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark

IPC: F01D11/08

Abstract: A blade outer air seal assembly includes a seal segment that has a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first wall is axially spaced from a second wall. The first and second walls extend from the base portion to an outer wall to define a circumferentially extending seal passage. A wear liner is within the seal passage.

公开(公告)号：US20200291805A1

公开(公告)日：2020-09-17

申请号：US16352432

申请日：2019-03-13

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Daniel J. Whitney ,  William M. Barker

IPC: F01D11/08

Abstract: A blade outer air seal includes a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first wall is axially spaced from a second wall. The first and second walls extend from the base portion to an outer wall. A rib extends from the base portion to the outer wall and spaced axially between the first and second walls.

公开(公告)号：US20200224555A1

公开(公告)日：2020-07-16

申请号：US16249303

申请日：2019-01-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas E. Clark ,  Dean W. Johnson

IPC: F01D25/28 ,  F01D11/08

Abstract: A blade outer air seal retention assembly may comprise a forward retention ring and an aft retention ring coupled to the forward retention ring. The forward retention ring may comprise a first shiplap flange extending aft from the forward retention ring. The aft retention ring may comprise a second shiplap flange extending forward from the aft retention ring.

公开(公告)号：US20200224544A1

公开(公告)日：2020-07-16

申请号：US16244409

申请日：2019-01-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William M. Barker ,  Daniel J. Whitney ,  Michael G. McCaffrey ,  Thomas E. Clark

IPC: F01D11/08 ,  F01D25/24

Abstract: A blade outer air seal assembly may comprise a blade outer air seal segment and a blade outer air seal support coupled to the blade outer air seal segment. The blade outer air seal segment may comprise a forward rail and an aft rail. The forward rail may be castellated. The blade outer air seal support may comprise an aft flange and a first forward flange. A pin may be disposed through the aft rail, the aft flange, the first forward flange, and the forward rail.

公开(公告)号：US10648407B2

公开(公告)日：2020-05-12

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：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.