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公开(公告)号：US10047609B2
公开(公告)日：2018-08-14
申请号：US14427145
申请日：2013-02-22
Applicant: United Technologies Corporation
Inventor： Thomas B. Hyatt , Carl Brian Klinetob
Abstract: An airfoil array includes a plurality of airfoils that differ in geometry over a plurality of geometry classes. An airfoil can include an airfoil body that has a first distinct piece and a second distinct piece that seats together with the first distinct piece. The first distinct piece and the second distinct piece include a mistake-proof feature configured such that the second distinct piece fully seats with the first distinct piece.
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公开(公告)号：US09422821B2
公开(公告)日：2016-08-23
申请号：US14776341
申请日：2014-03-14
Applicant: United Technologies Corporation
Inventor： Thomas B. Hyatt , Carl Brian Klinetob
CPC classification number: F01D9/042 , B64D45/02 , F01D5/288 , F01D25/005 , F01D25/243 , F05D2220/327 , F05D2260/31 , F05D2300/17 , F05D2300/173 , F05D2300/174 , F05D2300/50
Abstract: A device for providing a grounding path between an outer surface of a gas turbine aircraft engine and an inner surface of a gas turbine aircraft engine uses a structural guide vane (SGV) with a nonconductive coating on the surface. Bolts are put in bolt holes that have a bolt receiving cavity without the nonconductive coating. A washer and bolt are used so that attachment of the SGV to a surface provides a ground path from the SGV through the bolt, washer and nut for electrical engagement with a surface to which the bolt attaches the SGV.
Abstract translation: 用于在燃气涡轮机飞行器发动机的外表面和燃气涡轮机飞机发动机的内表面之间提供接地路径的装置使用在表面上具有非导电涂层的结构导叶（SGV）。 螺栓被放入螺栓孔中，螺栓孔具有不带非导电涂层的螺栓接收腔。 使用垫圈和螺栓，使得SGV附接到表面提供了从SGV通过螺栓，垫圈和螺母的接地路径，用于与螺栓附接到SGV的表面电接合。
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公开(公告)号：US20150361807A1
公开(公告)日：2015-12-17
申请号：US14765138
申请日：2014-03-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas B. Hyatt , Carl Brian Klinetob , Jason Leroux
CPC classification number: F01D9/04 , F01D25/162 , F01D25/246 , F02C3/04 , F02C7/20 , Y02T50/671
Abstract: A guide vane for use in a gas turbine engine fan section has an airfoil extending between a radially inner platform and a radially outer platform. The radially inner platform has a radially outwardly facing surface from which the airfoil extends and a radially inwardly facing underside. The airfoil has a trailing edge extending to a leading edge. The underside is attached to a mount bracket and a main rib extending from the underside of the platform adjacent the trailing edge and in a direction generally towards the leading edge, and merging into a top surface on the mount bracket. A pair of shoulders is formed on each of two circumferential sides of the rib. Each of the shoulders is spaced from each other at a point on the shoulders connected into the top surface of the mount bracket. The shoulders extend circumferentially toward each other and the under surface.
Abstract translation: 用于燃气涡轮发动机风扇部分的导向叶片具有在径向内部平台和径向外部平台之间延伸的翼型件。 径向内部平台具有径向向外的表面，翼面从该表面延伸并且径向向内面向下。 翼型件具有延伸到前缘的后缘。 下侧附接到安装支架和从平台的下侧延伸的主肋邻近后缘并且大致朝向前缘的方向，并且合并到安装支架上的顶表面中。 在肋的两个圆周侧的每一个上形成一对肩部。 每个肩部在连接到安装支架顶表面的肩部上的一个点处彼此间隔开。 肩部朝向彼此和下表面周向延伸。
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公开(公告)号：US09932842B2
公开(公告)日：2018-04-03
申请号：US14776382
申请日：2014-03-12
Applicant: United Technologies Corporation
Inventor： Thomas B. Hyatt , Carl Brian Klinetob
CPC classification number: F01D5/288 , F01D5/147 , F01D5/16 , F01D25/005 , F01D25/007 , F01D25/162 , F02C7/20 , F05D2220/32 , F05D2220/36 , F05D2230/90 , F05D2240/121 , F05D2240/123 , F05D2240/124 , F05D2300/611 , Y02T50/671 , Y02T50/673
Abstract: A structural guide vane for use in a gas turbine engine has a leading edge section, a trailing edge, a pressure surface and a suction surface. An erosion coating such as polyurethane resin is on the pressure surface and the suction surface. The leading edge of the vane is without the erosion coating and is bare metal. The vane is formed to include a plurality of pockets and bond shelves in the pressure surface side, and an epoxy bond line on the bond shelves holding a cover plate protected by the erosion coating.
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公开(公告)号：US20140086737A1
公开(公告)日：2014-03-27
申请号：US13712155
申请日：2012-12-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas B. Hyatt , Carl Brian Klinetob , Jason Leroux
IPC: F01D9/02
CPC classification number: F01D9/02 , F01D5/147 , F01D9/041 , F01D25/162 , F05D2220/36 , F05D2230/60 , F05D2240/12 , F05D2240/124 , Y02T50/40 , Y02T50/671 , Y02T50/673 , Y10T29/49323
Abstract: A disclosed structural guide vane for a gas turbine engine includes a strut defining a plurality of channels and a cover attached over the plurality of channels. The strut includes a first side defining a first surface of an airfoil and a second side including a plurality of channels. At least one of the plurality of channels defines a wall thickness of a portion of the first side that varies in a chord wise direction.
Abstract translation: 公开的用于燃气涡轮发动机的结构导叶包括限定多个通道的支柱和附接在多个通道上的盖。 支柱包括限定翼型件的第一表面的第一侧和包括多个通道的第二侧。 多个通道中的至少一个限定了第一侧的沿弦弦方向变化的一部分的壁厚。
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Patent Agency Ranking
公开(公告)号：US10260372B2
公开(公告)日：2019-04-16
申请号：US14609167
申请日：2015-01-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Carl Brian Klinetob , William Richard Ganoe, Jr. , Thomas B. Hyatt , Jason Leroux , Douglas J. Morgan
Abstract: A vibration damping assembly and a method of damping vibration in a gas turbine engine are disclosed. The vibration damping assembly includes a strut configured to couple a fan case and turbine engine case of a turbine engine, a strut cavity disposed within the strut, and vibration damping media disposed in the strut cavity.
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公开(公告)号：US20160032744A1
公开(公告)日：2016-02-04
申请号：US14776341
申请日：2014-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas B. Hyatt , Carl Brian Klinetob
CPC classification number: F01D9/042 , B64D45/02 , F01D5/288 , F01D25/005 , F01D25/243 , F05D2220/327 , F05D2260/31 , F05D2300/17 , F05D2300/173 , F05D2300/174 , F05D2300/50
Abstract: A device for providing a grounding path between an outer surface of a gas turbine aircraft engine and an inner surface of a gas turbine aircraft engine uses a structural guide vane (SGV) with a nonconductive coating on the surface. Bolts are put in bolt holes that have a bolt receiving cavity without the nonconductive coating. A washer and bolt are used so that attachment of the SGV to a surface provides a ground path from the SGV through the bolt, washer and nut for electrical engagement with a surface to which the bolt attaches the SGV.
Abstract translation: 用于在燃气涡轮机飞行器发动机的外表面和燃气涡轮机飞机发动机的内表面之间提供接地路径的装置使用在表面上具有非导电涂层的结构导叶（SGV）。 螺栓被放入螺栓孔中，螺栓孔具有不带非导电涂层的螺栓接收腔。 使用垫圈和螺栓，使得SGV附接到表面提供了从SGV通过螺栓，垫圈和螺母的接地路径，用于与螺栓附接到SGV的表面电接合。
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公开(公告)号：US20150252679A1
公开(公告)日：2015-09-10
申请号：US14427323
申请日：2013-03-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew Pope , David J. Yudichak , John P. Lucashu , Gregory E. Reinhardt , John C. Ditomasso , Steven L. Conner , Carl Brian Klinetob , Jason Leroux
CPC classification number: F01D9/02 , F01D1/02 , F01D5/147 , F01D9/041 , F05D2230/23 , F05D2240/12 , Y02T50/671
Abstract: A static guide vane for use in a fan section of a gas turbine engine includes an outer platform and an inner platform. The inner and outer platforms are connected by an airfoil. The airfoil have channels extending into a main body of the airfoil to reduce the weight of the vane. A cover closes off the channels with the cover providing a portion of the airfoil.
Abstract translation: 用于燃气涡轮发动机的风扇部分的静态导向叶片包括外平台和内平台。 内外平台通过翼型连接。 翼型件具有延伸到翼型件的主体中的通道，以减小叶片的重量。 盖子封闭通道，盖子提供翼型的一部分。
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9.发明申请AIRFOIL ARRAY WITH AIRFOILS THAT DIFFER IN GEOMETRY ACCORDING TO GEOMETRY CLASSES 审中-公开具有与几何类别不同的几何尺寸的气翼阵列的气翼阵列公开(公告)号：US20150226067A1
公开(公告)日：2015-08-13
申请号：US14427145
申请日：2013-02-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas B. Hyatt , Carl Brian Klinetob
CPC classification number: F01D5/141 , B23P15/04 , F01D5/147 , F01D5/18 , F01D5/28 , F01D9/041 , F05D2230/64 , Y02T50/672 , Y02T50/673 , Y10T29/49321
Abstract: An airfoil array includes a plurality of airfoils that differ in geometry over a plurality of geometry classes. An airfoil can include an airfoil body that has a first distinct piece and a second distinct piece that seats together with the first distinct piece. The first distinct piece and the second distinct piece include a mistake-proof feature configured such that the second distinct piece fully seats with the first distinct piece.
Abstract translation: 翼型阵列包括在多个几何类别上几何形状不同的多个翼型件。 翼型件可以包括翼型件本体，其具有与第一不同件对准的第一不同件和第二不同件。 第一个不同的部分和第二个不同的部分包括防错特征，其被配置成使得第二个不同的部分完全与第一个不同的部分座位。
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公开(公告)号：US10167737B2
公开(公告)日：2019-01-01
申请号：US14433861
申请日：2013-03-12
Applicant: United Technologies Corporation
Inventor： Gregory E. Reinhardt , Paul Thomas Rembish , Steven L. Conner , Thomas B. Hyatt , Steven J. Feigleson , Carl Brian Klinetob
Abstract: A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.
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