公开(公告)号：US11454130B2

公开(公告)日：2022-09-27

申请号：US16567541

申请日：2019-09-11

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark ,  William Wangard, III ,  Danielle Mahoney

IPC: F01D11/08 ,  F02C7/28

Abstract: A blade outer air seal includes a carrier that has a dovetail and a ceramic seal segment supported on the dovetail. The ceramic seal segment has first and second axial ends, first and second circumferential sides, an inner side, an outer side, and first and second inward-facing dovetail hooks that project from the outer side and define a dovetail key. The ceramic seal segment is axially receivable onto the dovetail of the carrier via the dovetail key.

公开(公告)号：US11261971B2

公开(公告)日：2022-03-01

申请号：US16679822

申请日：2019-11-11

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Caleb J. Farley

IPC: F16J15/3288 ,  F01D11/00 ,  F01D11/08

Abstract: A brush seal includes a first plate and a second plate. A plurality of bristles have a first end and a second end. The plurality of bristles are arranged between the first and second plates such that the first and second ends extend beyond the first and second plates. The first end is arranged at an angle relative to the second end.

公开(公告)号：US11248480B2

公开(公告)日：2022-02-15

申请号：US16567492

申请日：2019-09-11

Applicant: United Technologies Corporation

Inventor： Sudarshan Thirumalai ,  William M. Barker ,  Thomas E. Clark

IPC: F01D11/00

Abstract: A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a carrier. At least two of the plurality of segments have a first wall and a second wall circumferentially spaced from one another and a base portion that extends from the first wall to the second wall. The base portion extends circumferentially outward past the first and second walls to form first and second sealing surfaces. An intersegment seal has a curved surface. The curved surface is engaged with the first and second sealing surfaces between the at least two segments.

公开(公告)号：US11187100B2

公开(公告)日：2021-11-30

申请号：US16207918

申请日：2018-12-03

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark

IPC: F01D11/12 ,  C04B38/00

Abstract: A method of forming a blade outer air seal includes applying a cavity layer that has a plurality of cavities to a radially inner side of a seal body. The cavity layer is coated with an abradable coating.

公开(公告)号：US20210140546A1

公开(公告)日：2021-05-13

申请号：US16679822

申请日：2019-11-11

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Caleb J. Farley

IPC: F16J15/3288 ,  F01D11/00

Abstract: A brush seal includes a first plate and a second plate. A plurality of bristles have a first end and a second end. The plurality of bristles are arranged between the first and second plates such that the first and second ends extend beyond the first and second plates. The first end is arranged at an angle relative to the second end.

公开(公告)号：US10934876B2

公开(公告)日：2021-03-02

申请号：US16038480

申请日：2018-07-18

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark

IPC: F01D11/08

Abstract: A gas turbine engine includes a turbine section including at least one turbine rotor having at least one blade. A blade outer air seal is positioned radially outward of a radially outer tip of the at least one turbine blade. The blade outer air seal has a forward hook and an aft hook. The forward hook is supported on a forward retainer and the aft hook is supported on an aft hook retainer. The aft hook retainer provides structure to prevent rotation of the blade outer air seal relative to the aft hook retainer. There is an interference fit between the aft hook retainer and the forward retainer. A load path is provided from a static structure through the aft hook retainer to the forward retainer.

公开(公告)号：US10787923B2

公开(公告)日：2020-09-29

申请号：US16113836

申请日：2018-08-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas E Clark ,  William M. Barker

IPC: F01D11/00 ,  F01D11/08

Abstract: A seal for a gas turbine engine is disclosed. In various embodiments, the seal includes a first annular ring; a second annular ring; an annular brush having a first brush end disposed between the first annular ring and the second annular ring; and an axial ring seal having a first seal end configured for contact with the second annular ring.

公开(公告)号：US10753221B2

公开(公告)日：2020-08-25

申请号：US16217402

申请日：2018-12-12

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark

IPC: F01D11/08

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body extending circumferentially between opposed mate faces and at least one rail extending outwardly from the seal body. The seal body has a seal face that bounds a gas path. At least one rail aperture is defined at least partially through the at least one rail. At least one wear liner has a liner body. The liner body defines a liner aperture and an outer periphery that mates with the at least one rail aperture. A seal support is mountable to an engine case. The seal support has at least one support hook that mates with the liner aperture to mount the seal to the seal support. A method of assembly for a gas turbine engine is also disclosed.

公开(公告)号：US20200149477A1

公开(公告)日：2020-05-14

申请号：US16246756

申请日：2019-01-14

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark ,  Winston G. Smiddy

IPC: F02C7/28 ,  F01D11/12 ,  F01D11/00

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body extending circumferentially between opposed mate faces, the seal body having a seal face that bounds a gas path and an opposed impingement face, a seal carrier extending along the impingement face, and a seal member trapped between the seal carrier and the impingement face such that the seal member is circumferentially aligned with one of the mate faces. A method of sealing is also disclosed.

公开(公告)号：US20200080437A1

公开(公告)日：2020-03-12

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.