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公开(公告)号：US11242991B2
公开(公告)日：2022-02-08
申请号：US16413174
申请日：2019-05-15
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , Kathryn S. Read , William M. Barker
IPC: C04B35/80 , F23R3/00 , C04B35/628
Abstract: A method of manufacturing a component includes forming an inner wrap about a mandrel. The inner wrap has first and second walls joined by a base portion and an outer wall. A rod is arranged at each of the first and second walls. An outer wrap is formed about the inner wrap and the rods to form a body. Features are formed in the first and second walls.
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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：US11035243B2
公开(公告)日：2021-06-15
申请号：US15995328
申请日：2018-06-01
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , Kevin D. Tracy
Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a support mountable to an engine static structure. The support has a main body extending axially between leading and trailing edge portions and circumferentially between opposed mate faces, and the main body includes a pair of opposed retention hooks extending inwardly from the leading and trailing edge portions to bound an elongated groove extending circumferentially between the opposed mate faces. A seal has a sealing portion that extends from an engagement portion. The sealing portion has a sealing face that extends circumferentially between first and second mate faces. An overwrap has one or more plies that follow a perimeter of the engagement portion to define an interface between the retention hooks and the engagement portion. A method of sealing is also disclosed.
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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：US10989059B2
公开(公告)日：2021-04-27
申请号：US16380506
申请日：2019-04-10
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , William M. Barker
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 hook extends from the base portion and circumferentially spaced from a second hook. The first and second hooks extend along an axial length of the base portion. The first circumferential side has a protrusion and the second circumferential side has a groove.
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公开(公告)号：US10968772B2
公开(公告)日：2021-04-06
申请号：US16042096
申请日：2018-07-23
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark
Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a chamber within the attachment block, and communicates to circumferential edges of the attachment block to direct cooling air along the central web of the blade outer air seal. A blade outer air seal assembly is also disclosed.
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公开(公告)号：US20210079803A1
公开(公告)日：2021-03-18
申请号：US16570338
申请日：2019-09-13
Applicant: United Technologies Corporation
Inventor： Dean W. Johnson , Thomas E. Clark
Abstract: A blade outer air seal includes a base portion. A first wall and a second wall extend radially from the base portion. The first wall is axially spaced from the second wall. The first and second walls extend in a circumferential direction. A first hook extends from the first wall and a second hook extends from the second wall. The first and second hooks extend in an axial direction towards one another to form a passage that extends in the circumferential direction. The passage is configured to receive a carrier. A tab extends radially outward from the second hook. The tab is configured to engage with the carrier.
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公开(公告)号：US20210071584A1
公开(公告)日：2021-03-11
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
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.
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公开(公告)号：US10927694B2
公开(公告)日：2021-02-23
申请号：US16352150
申请日：2019-03-13
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , William M. Barker
Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of seal segments arranged circumferentially about an axis and mounted in the support structure by a carrier. A coverplate is arranged between the carrier and at least one of the plurality of seal segments. The coverplate forms a first passage between the coverplate and the carrier and a second passage between the coverplate and the seal segment.
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