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公开(公告)号：US10161254B2
公开(公告)日：2018-12-25
申请号：US14773475
申请日：2013-10-22
Applicant: United Technologies Corporation
Inventor： Thomas B. Hyatt , William Richard Ganoe, Jr.
Abstract: A method of forming a guide vane is disclosed. The method includes forming a vane blank with sufficient material to fabricate the guide vane in accordance with any one of a plurality of different vane classes. The vane blank is inspected for material inconsistencies, and material is removed from the vane blank to form a desired guide vane in accordance with one of the plurality of vane classes. The inspection process includes disregarding at least one material inconsistency in a region of the vane blank that is removed to form the guide vane.
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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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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：US09926965B2
公开(公告)日：2018-03-27
申请号：US14731584
申请日：2015-06-05
Applicant: United Technologies Corporation
Inventor： Thomas B. Hyatt
CPC classification number: F16B43/004 , F01D25/243 , F16B5/0258 , F16B19/02 , F16B35/041 , F16B35/048
Abstract: A fastener includes a fastening portion including a head, a threaded portion having a first diameter, and a shank having a second diameter that is less than the first diameter. The shank is located between the head and the threaded portion. A sleeve surrounds the shank. The sleeve and the shank are uncoupled.
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Patent Agency Ranking
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：US20150233264A1
公开(公告)日：2015-08-20
申请号：US14620292
申请日：2015-02-12
Applicant: United Technologies Corporation
Inventor： Thomas B. Hyatt , William Richard Ganoe, JR.
CPC classification number: F01D25/04 , B23P15/04 , B25B11/002 , F01D5/16 , F01D9/02 , F05D2230/10 , F05D2230/23 , F05D2260/96 , F05D2300/121 , F05D2300/507 , F16F7/01 , Y02T50/672 , Y10T29/49231
Abstract: An example method of assembling a particle damped gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, holding damping media within a cavity of a gas turbine engine component using magnetic force.
Abstract translation: 根据本公开的示例性方面的组装颗粒阻尼燃气涡轮发动机部件的示例性方法包括使用磁力将阻尼介质保持在燃气涡轮发动机部件的空腔内。
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8.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：US10087766B2
公开(公告)日：2018-10-02
申请号：US14765274
申请日：2014-03-10
Applicant: United Technologies Corporation
Inventor： Andrew Pope , John P. Lucashu , Jason Leroux , Carl Brian Klinetob , Thomas B. Hyatt
IPC: F03D11/04 , F03B3/18 , F03D1/04 , F03D3/04 , F01D9/02 , F01D9/04 , F01D25/24 , F01D25/28 , F02C7/20
Abstract: A guide vane includes an airfoil with a first end and a second end. A platform is disposed at a first end of the airfoil, and a K-gusset is disposed on the platform opposite the airfoil. The K-gusset includes four bosses and ribs extending between the bosses in a “K” configuration.
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公开(公告)号：US09963984B2
公开(公告)日：2018-05-08
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.
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