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公开(公告)号：US10927710B2
公开(公告)日：2021-02-23
申请号：US16142515
申请日：2018-09-26
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark , Daniel J. Whitney
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.
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公开(公告)号：US20200040757A1
公开(公告)日：2020-02-06
申请号：US16055636
申请日：2018-08-06
Applicant: United Technologies Corporation
Inventor： William M. Barker , Thomas E. Clark , Daniel J. Whitney
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, and the forward and aft hooks are supported on forward and aft seal hooks of an attachment. The blade outer air seal is formed of a plurality of laminate layered with a central web formed of a plurality of laminate members including an inner reinforcement member. An outer overwrap wraps around the inner reinforcement member. A method is also disclosed.
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公开(公告)号：US11111806B2
公开(公告)日：2021-09-07
申请号：US16055511
申请日：2018-08-06
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , William M. Barker , Daniel J. Whitney
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, and the forward and aft hooks are supported on forward and aft seal hooks of an attachment block. The blade outer air seal forward and aft hooks extend at angles relative to an upper surface of a web that is between 20 and 70 degrees. A method is also disclosed.
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公开(公告)号：US11085316B2
公开(公告)日：2021-08-10
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：US11015473B2
公开(公告)日：2021-05-25
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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Patent Agency Ranking
公开(公告)号：US20200040756A1
公开(公告)日：2020-02-06
申请号：US16055511
申请日：2018-08-06
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , William M. Barker , Daniel J. Whitney
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, and the forward and aft hooks are supported on forward and aft seal hooks of an attachment block. The blade outer air seal forward and aft hooks extend at angles relative to an upper surface of a web that is between 20 and 70 degrees. A method is also disclosed.
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公开(公告)号：US20200003066A1
公开(公告)日：2020-01-02
申请号：US16019936
申请日：2018-06-27
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , Daniel J. Whitney
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.
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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
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.
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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
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.
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公开(公告)号：US10815810B2
公开(公告)日：2020-10-27
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
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.
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