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公开(公告)号：US09879558B2
公开(公告)日：2018-01-30
申请号：US14766469
申请日：2014-02-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark J Rogers , Mark Broomer , Craig R. McGarrah , Timothy M Davis , Anthony B Swift , Russell E Keene , Carson A. Roy Thill , Timothy A. Dunbar
CPC classification number: F01D11/08 , F01D25/246 , F05D2220/32 , F05D2230/60 , F05D2240/10 , F05D2240/20 , F05D2240/55 , F05D2250/14
Abstract: An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.
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公开(公告)号：US09670791B2
公开(公告)日：2017-06-06
申请号：US14772194
申请日：2014-03-04
Applicant: United Technologies Corporation
Inventor： Mark Broomer , Carson A. Roy Thill , Timothy M. Davis , Anthony P. Cherolis , Robert L. Hazzard , Craig R. McGarrah , Conway Choung , Russell E. Keene
CPC classification number: F01D11/08 , F01D5/14 , F01D9/02 , F01D11/003 , F01D11/005 , F01D25/246
Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a flexible seal that is attached to the first component. The flexible seal at least partially seals a gap between the first component and the second component. The flexible seal includes a mount and a finger seal that sealingly engages the second component. The mount includes a boss that sealingly engages the first component.
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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：US10145308B2
公开(公告)日：2018-12-04
申请号：US14611920
申请日：2015-02-02
Applicant: United Technologies Corporation
Inventor： Carson A. Roy Thill , Mark Broomer , Timothy M. Davis , Craig R. McGarrah , Mark J. Rogers , Russell E. Keene , Anthony B. Swift
Abstract: A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.
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Patent Agency Ranking
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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7.发明申请公开(公告)号：US20160003081A1
公开(公告)日：2016-01-07
申请号：US14772194
申请日：2014-03-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark Broomer , Carson A. Roy Thill , Timothy M. Davis , Anthony P. Cherolis , Robert L. Hazzard , Craig R. McGarrah , Conway Choung , Russell E. Keene
CPC classification number: F01D11/08 , F01D5/14 , F01D9/02 , F01D11/003 , F01D11/005 , F01D25/246
Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a flexible seal that is attached to the first component. The flexible seal at least partially seals a gap between the first component and the second component. The flexible seal includes a mount and a finger seal that sealingly engages the second component. The mount includes a boss that sealingly engages the first component.
Abstract translation: 用于涡轮发动机的组件包括涡轮发动机第一部件，涡轮发动机第二部件和附接到第一部件的柔性密封件。 柔性密封件至少部分地密封第一部件和第二部件之间的间隙。 柔性密封件包括安装件和密封地接合第二部件的手指密封件。 安装件包括密封地接合第一部件的凸台。
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公开(公告)号：US10731493B2
公开(公告)日：2020-08-04
申请号：US14783048
申请日：2014-04-10
Applicant: United Technologies Corporation
Inventor： Timothy M. Davis , Mark J. Rogers , Mark Broomer , Craig R. McGarrah , Carson A. Roy Thill
Abstract: A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.
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公开(公告)号：US20160061047A1
公开(公告)日：2016-03-03
申请号：US14783048
申请日：2014-04-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Timothy M. Davis , Mark J. Rogers , Mark Broomer , Craig R. McGarrah , Carson A. Roy Thill
Abstract: A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.
Abstract translation: 用于将燃气涡轮发动机定子的径向外部部件密封到其径向内部部件的密封件包括轴向弹性的密封载体，其适于安装密封载体并且在其径向内部包括一对径向间隔开的轴向延伸的， 径向弹性夹爪，其适于将密封元件（例如其间的绳索密封件）与发动机定子的径向内部部件密封接合。
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公开(公告)号：US20180328228A1
公开(公告)日：2018-11-15
申请号：US15919832
申请日：2018-03-13
Applicant: United Technologies Corporation
Inventor： Joseph F. Englehart , Craig R. McGarrah
CPC classification number: F01D9/042 , F01D11/005 , F05D2240/12 , F05D2240/55 , F05D2260/30
Abstract: A vane assembly includes an outer platform, an inner platform, and a vane. The inner platform has an inner flange that includes a first face, a second face disposed opposite the first face, a third face extending from the first face towards the second face, and a fourth face extending from the third face towards a tip of the inner flange. The third face and the fourth face at least partially define a first notch.
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