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公开(公告)号：US20210017874A1
公开(公告)日：2021-01-21
申请号：US16517009
申请日：2019-07-19
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark
IPC: F01D11/08
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 support structure via a carrier. At least one of the segments have a first hook circumferentially spaced from a second hook. A base portion extends from the first hook to the second hook. The carrier has a cavity on a radially inner surface between the carrier and the base portion.
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公开(公告)号：US20210017872A1
公开(公告)日：2021-01-21
申请号：US16516943
申请日：2019-07-19
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Thomas E. Clark
IPC: F01D11/08
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 support structure. At least two of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. A first hook extends from the first wall and a second hook extends from the second wall. A wedge seal is arranged between the at least two adjacent seal segments. A clip is configured to bias the wedge seal radially inward.
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公开(公告)号：US20200325789A1
公开(公告)日：2020-10-15
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：US20200308973A1
公开(公告)日：2020-10-01
申请号：US16371330
申请日：2019-04-01
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , William M. Barker
IPC: F01D11/08
Abstract: A blade outer air seal assembly includes a blade outer air seal segment that has a base portion that extends from a first axial side to a second axial side and from a first circumferential side to a second circumferential side. An intersegment seal is arranged adjacent the first circumferential side. The intersegment seal has a first seal portion and a second seal portion connected by a rib.
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公开(公告)号：US20200300106A1
公开(公告)日：2020-09-24
申请号：US16795738
申请日：2020-02-20
Applicant: United Technologies Corporation
Inventor： William M. Barker , Thomas E. Clark
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.
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Patent Agency Ranking
公开(公告)号：US20200072070A1
公开(公告)日：2020-03-05
申请号：US16122373
申请日：2018-09-05
Applicant: United Technologies Corporation
Inventor： Ken F. Blaney , Paul M. Lutjen , Thomas E. Clark
Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section has at least one turbine rotor that has a radially extending turbine blade and is rotatable about an axis of rotation and at least one turbine vane. A blade outer air seal is positioned radially outwardly of a radially outer tip of the turbine blade. A structure mounts the blade outer air seal and provides a platform of at least one turbine vane.
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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：US20200025028A1
公开(公告)日：2020-01-23
申请号：US16042066
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 central chamber within the attachment block, and communicates with cooling holes through a radially inner face of the attachment block to direct cooling air at the central web of the blade outer air seal. A blade outer air seal 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：US10443732B2
公开(公告)日：2019-10-15
申请号：US15075955
申请日：2016-03-21
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , Eric Charles Mundell , Gary L. Grogg
Abstract: Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L) such that a ratio (L/R) is between 0.8 and 1.4, the annular radial member disposed at a first angle with respect to the outer axially extending member, a heat shield in mechanical communication with the seal runner, and a volume bounded by an outer face of the annular radial member and an inner face of the heat shield. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.
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