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：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：US20200072069A1

公开(公告)日：2020-03-05

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：US20200040751A1

公开(公告)日：2020-02-06

申请号：US16050625

申请日：2018-07-31

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark

IPC: F01D11/00 ,  F01D11/08

Abstract: A gas turbine engine includes a turbine section having a turbine rotor and at least one blade extending outwardly of the turbine rotor. The turbine rotor rotates about an axis of rotation. A blade outer air seal is positioned radially outward of the at least one blade. The blade outer air seal has an axially forward hook and an axially aft hook supported to static structure. An axial seal is attached to static structure forward of the forward hook, and has a sealing portion extending in an aft direction. A sealing surface member is positioned intermediate an aft end of the axial seal and a forward end of the forward hook to provide a sealing surface for sealing between the seal and the blade outer air seal.

公开(公告)号：US20190292927A1

公开(公告)日：2019-09-26

申请号：US15927145

申请日：2018-03-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William M. Barker

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

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes a seal segment. The seal segment includes a blade-sealing portion that provides an elongated slot, a flange that extends from the blade-sealing portion, and a hook that extends from the blade-sealing portion and is spaced from the flange. The hook has a surface that at least partially provides a cavity. A feather seal has an elongated portion and first and second legs which extend from the elongated portion. The first leg abuts the flange, the second leg is disposed in the cavity, and the elongated portion is disposed in the elongated slot.

公开(公告)号：US11578609B2

公开(公告)日：2023-02-14

申请号：US16785161

申请日：2020-02-07

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Daniel J. Whitney ,  Kathryn S. Read ,  Andrew J. Lazur ,  William M. Barker

IPC: F01D11/12 ,  B28B1/00 ,  F01D25/12

Abstract: A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.

公开(公告)号：US11255209B2

公开(公告)日：2022-02-22

申请号：US16555235

申请日：2019-08-29

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  William M. Barker

IPC: F01D11/08 ,  F01D5/14 ,  F01D9/04

Abstract: A blade outer air seal assembly includes a carrier that has a slot and a hole that extends into the slot. A blade outer air seal has a plurality of segments that extend circumferentially about an axis and mounted in the carrier. At least one of the plurality of segments has a base portion and a first wall that extends axially and radially outwardly from the base portion. The first wall has an aperture. A pin extends through the hole and the aperture.

公开(公告)号：US10961861B2

公开(公告)日：2021-03-30

申请号：US16055576

申请日：2018-08-06

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  William M. Barker

IPC: F01D11/08 ,  F02C7/28 ,  F01D25/24 ,  F01D11/22

Abstract: A gas turbine engine turbine section includes at least one blade extending radially outwardly to an outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip. The blade outer air seal has forward and aft hooks. The forward and aft hooks are supported on forward and aft seal hooks of an attachment block. The attachment block has a forward case mount hook and an aft case mount hook. The attachment block is supported on a forward case hook and an aft case hook of a static casing within the engine. The forward case mount hook and the aft case mount hook on the attachment block face in a common axial direction. The forward case hook and the aft case hook face in a common axial direction which is opposed to the common axial direction. A method is also disclosed.

公开(公告)号：US20210079804A1

公开(公告)日：2021-03-18

申请号：US16785161

申请日：2020-02-07

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Daniel J. Whitney ,  Kathryn S. Read ,  Andrew J. Lazur ,  William M. Barker

IPC: F01D11/12 ,  F01D25/12 ,  B28B1/00

Abstract: A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.