公开(公告)号：US11047250B2

公开(公告)日：2021-06-29

申请号：US16376210

申请日：2019-04-05

Applicant: United Technologies Corporation

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

IPC: F01D11/08 ,  F01D25/12 ,  F01D25/24

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. The second wall has at least one wall window configured to engage with a support structure. An outer wall radially spaced from the base portion between the first and second walls. The outer wall has at least one outer wall window configured to engage with the support structure.

公开(公告)号：US20200318491A1

公开(公告)日：2020-10-08

申请号：US16376210

申请日：2019-04-05

Applicant: United Technologies Corporation

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

IPC: F01D11/08 ,  F01D25/12 ,  F01D25/24

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. The second wall has at least one wall window configured to engage with a support structure. An outer wall radially spaced from the base portion between the first and second walls. The outer wall has at least one outer wall window configured to engage with the support structure.

公开(公告)号：US20200300108A1

公开(公告)日：2020-09-24

申请号：US16356111

申请日：2019-03-18

Applicant: United Technologies Corporation

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

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 carrier has a platform. A portion of the platform is within the seal passage. A radially extending first hook protrudes from the platform and is configured to engage with a support structure.

公开(公告)号：US20200300107A1

公开(公告)日：2020-09-24

申请号：US16356097

申请日：2019-03-18

Applicant: United Technologies Corporation

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

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. An outer wall joins the first and second walls. The outer wall has a first edge and a second edge. Each of the edges have a first portion and a second portion arranged at a first angle relative to the first portion.

公开(公告)号：US10753220B2

公开(公告)日：2020-08-25

申请号：US16019936

申请日：2018-06-27

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Daniel J. Whitney

IPC: F01D11/08 ,  F01D25/00 ,  F01D25/18 ,  F01D25/24

Abstract: A blade outer air seal includes a base portion that extends between a leading edge and a trailing edge. A forward wall and an aft wall extend radially outward from the base portion to a radially outer portion. The radially outer portion is spaced from the base portion.

公开(公告)号：US20200063592A1

公开(公告)日：2020-02-27

申请号：US16108335

申请日：2018-08-22

Applicant: United Technologies Corporation

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

IPC: F01D11/08 ,  F02C7/20

Abstract: A gas turbine engine includes a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is positioned radially outwardly of the radially outer tip of the turbine blade. The blade outer air seal has a forward hook at an axially forward location and an aft hook at an axially aft location. An axial direction is defined by a rotational axis of the turbine blade. The blade outer air seal has a central web extending axially between the forward and aft hooks. The forward and aft hooks extend generally radially outward from the central web, and have slots for being received on forward and aft support hooks of a blade outer air seal support.

公开(公告)号：US11098608B2

公开(公告)日：2021-08-24

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 ,  B29C70/30 ,  F01D25/24

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：US11021987B2

公开(公告)日：2021-06-01

申请号：US16412737

申请日：2019-05-15

Applicant: United Technologies Corporation

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

IPC: F01D11/08 ,  F01D25/00

Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of segments that extend circumferentially about an axis and mounted in the support structure via a carrier. At least one of the plurality of segments 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 hook extends from the base portion near the first axial side and faces towards the second axial side. A second hook extends from the base portion near the second axial side and faces towards the first axial side. A slot is in the second hook configured to receive a pin.

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：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.