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公开(公告)号：US10968761B2
公开(公告)日：2021-04-06
申请号：US16246756
申请日：2019-01-14
Applicant: United Technologies Corporation
Inventor： William M. Barker , Thomas E. Clark , Winston G. Smiddy
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.
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公开(公告)号：US20210071541A1
公开(公告)日：2021-03-11
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.
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公开(公告)号：US20210062671A1
公开(公告)日：2021-03-04
申请号：US16555235
申请日：2019-08-29
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , William M. Barker
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.
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公开(公告)号：US20200347740A1
公开(公告)日：2020-11-05
申请号：US16402595
申请日：2019-05-03
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , William M. Barker
Abstract: A blade outer air seal assembly includes a blade outer air seal that has a plurality of seal segments that extend circumferentially about an axis and mounted in a support structure via a carrier. Each of the seal 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 and second hook extend along the base portion in an axial direction. The first and second hooks are engaged with the carrier. The carrier has a wall forward or aft of the first and second hooks and extends radially inward of the first and second hooks.
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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
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.
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Patent Agency Ranking
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.
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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.
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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
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.
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公开(公告)号：US20200063587A1
公开(公告)日：2020-02-27
申请号：US16113836
申请日：2018-08-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas E Clark , William M. Barker
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.
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公开(公告)号：US20200040755A1
公开(公告)日：2020-02-06
申请号：US16055576
申请日：2018-08-06
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , William M. Barker
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 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.
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