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Patent Agency Ranking
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：US10801342B2
公开(公告)日：2020-10-13
申请号：US14644596
申请日：2015-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark David Ring , Scot A Webb , Mark J Rogers , Gerald D Cassella , Charles H Warner , Eric A Kuehne , Jonathan J Earl , Matthew M Zietala , Neil L Tatman , Randall J Butcher , Matthew R Willett , Nicholas R Leslie
Abstract: A vane cluster for a gas turbine engine includes a first end-of-cluster vane, a second end-of-cluster vane, a neighbor vane adjacent to the second end-of-cluster vane at an interface that includes an angled load interface therebetween; and a multiple of base vanes between the first end-of-cluster vane and the neighbor vane, the angled load interface different than an interface between each of the multiple of base vane.
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公开(公告)号：US20160010482A1
公开(公告)日：2016-01-14
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
IPC: F01D11/08
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.
Abstract translation: 燃气涡轮发动机内的界面包括多个分段部件，每个部件具有多个孔的段凸缘，多个孔中的至少一个孔是第一槽孔。 具有环形凸缘的整个环形部件，其限定多个孔环，所述多个环形孔中的至少一个具有第二狭槽孔，所述第二狭缝孔横向于所述第一狭缝孔。
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公开(公告)号：US10371005B2
公开(公告)日：2019-08-06
申请号：US15215132
申请日：2016-07-20
Applicant: United Technologies Corporation
Inventor： Jeffrey D Ponchak , Mark J Rogers , James R Plante
Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield ply assembly defined about an axis; a second heat shield ply assembly defined about the axis, the second heat shield ply assembly receivable at least partially over the first heat shield assembly and a band clamp mounted to the second heat shield assembly to circumferentially retain the first heat shield ply assembly and the second heat shield ply assembly.
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公开(公告)号：US20180023417A1
公开(公告)日：2018-01-25
申请号：US15215132
申请日：2016-07-20
Applicant: United Technologies Corporation
Inventor： Jeffrey D Ponchak , Mark J Rogers , James R Plante
CPC classification number: F01D25/145 , F01D25/24 , F01D25/265 , F05D2220/32 , F05D2230/60 , F05D2260/231
Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield ply assembly defined about an axis; a second heat shield ply assembly defined about the axis, the second heat shield ply assembly receivable at least partially over the first heat shield assembly and a band clamp mounted to the second heat shield assembly to circumferentially retain the first heat shield ply assembly and the second heat shield ply assembly.
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