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公开(公告)号：US11619136B2
公开(公告)日：2023-04-04
申请号：US16434630
申请日：2019-06-07
Applicant: United Technologies Corporation
Inventor： Brian C. McLaughlin , Paul M. Lutjen , Richard K. Hayford , Anthony B. Swift
Abstract: A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss. The blade outer air seal segment further including a stress-relief recess. The stress-relief boss being located within the stress relief recess.
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公开(公告)号：US11591917B2
公开(公告)日：2023-02-28
申请号：US16434630
申请日：2019-06-07
Applicant: United Technologies Corporation
Inventor： Brian C. McLaughlin , Paul M. Lutjen , Richard K. Hayford , Anthony B. Swift
Abstract: A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss. The blade outer air seal segment further including a stress-relief recess. The stress-relief boss being located within the stress relief recess.
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Patent Agency Ranking
公开(公告)号：US11274566B2
公开(公告)日：2022-03-15
申请号：US16552347
申请日：2019-08-27
Applicant: United Technologies Corporation
Inventor： Christina G. Ciamarra , Anthony B. Swift
Abstract: A blade outer air seal for a gas turbine engine includes a platform having a leading edge and a trailing edge. A pair of circumferential edges connect the leading edge and the trailing edge. An end wall protrudes radially outward from the platform at the trailing edge. A first support rib connects one of the circumferential edges to the end wall and structurally supports the end wall. A first boss portion extends axially forward from the end wall and is disposed radially outward of the first support rib.
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公开(公告)号：US10526897B2
公开(公告)日：2020-01-07
申请号：US14870175
申请日：2015-09-30
Applicant: United Technologies Corporation
Inventor： Anthony B. Swift , Paul M. Lutjen
Abstract: A gas turbine engine component includes a wall portion that includes a first side and a second opposite side. A plurality of passages extends between the first side of the wall portion and the second side of the wall portion and includes a plurality of inlets located on the first side of the wall portion. A plurality of outlets are located on a second side of the wall portion. The plurality of outlets include a first plurality of outlets located on a first side of the plurality of inlets and a second plurality of outlets located on a second side of the plurality of inlets.
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公开(公告)号：US10138748B2
公开(公告)日：2018-11-27
申请号：US14997323
申请日：2016-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas J. Praisner , Paul M. Lutjen , Ken F. Blaney , Anthony B. Swift , Neil L. Tatman , Christopher M. Jarochym
Abstract: A gas turbine engine component is provided. The gas turbine engine component comprises a main body having a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The elongated transition portion has an axial length that is greater than a radial height. A gas turbine engine is also provided.
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公开(公告)号：US20180119560A1
公开(公告)日：2018-05-03
申请号：US15339581
申请日：2016-10-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jose R. Paulino , Ken F. Blaney , Terence P. Tyler, JR. , Daniel S. Rogers , Anthony B. Swift , Thomas E. Clark
CPC classification number: F01D11/10 , F01D9/02 , F01D11/003 , F01D11/14 , F01D25/14 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/55 , Y02T50/672 , Y02T50/675
Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.
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公开(公告)号：US20150226132A1
公开(公告)日：2015-08-13
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
CPC classification number: F02C7/28 , F01D11/005 , F01D25/24 , F01D25/246 , F02C3/04 , F05D2240/56 , F05D2240/58 , F05D2260/30 , F16J15/0887
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.
Abstract translation: 用于燃气涡轮发动机的密封组件包括发动机静止结构。 第一和第二构件将空腔彼此流体地分开。 密封组件由发动机结构捕获。 密封组件包括承载件和接合第一构件的密封件。 第二个成员由承运人捕获。
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