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公开(公告)号：US20190040744A1
公开(公告)日：2019-02-07
申请号：US15670654
申请日：2017-08-07
Applicant: United Technologies Corporation
Inventor： Daniel A. Bales , Dmitri Novikov , Robert C. Dolan , Kenneth A. Frisk , Steven T. Gordon , William R. Graves , Eric W. Malmborg , Francis B. Parisi , Randy P. Salva , Michael A. Weisse , Russell A. Beers , Xuedong Zhou , Christopher Treese , Tri Nguyen
Abstract: An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.
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公开(公告)号：US10060266B2
公开(公告)日：2018-08-28
申请号：US14768512
申请日：2013-11-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James Cosby , Michael A. Weisse , Kwan Hui
CPC classification number: F01D5/18 , B23P15/04 , F01D5/147 , F04D29/324 , F05D2220/32 , F05D2220/36 , F05D2230/23 , F05D2230/60 , Y02T50/671 , Y02T50/676
Abstract: Hollow fan blades for gas turbine engines are disclosed. The hollow fan blades include a body having a convex side and a concave side wherein the convex side has a cavity formed therein. The cavity is covered by two covers including an inner cover that may be adhered to the body of the fan blade assembly and an outer cover that may be adhered to the inner cover and/or the body of the fan blade assembly. The covers may be made of titanium, more than two covers may be employed and more than one cavity may be employed.
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公开(公告)号：US20180030995A1
公开(公告)日：2018-02-01
申请号：US15225448
申请日：2016-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael A. Weisse
Abstract: A fan blade includes a metallic body, a first composite cover, and a second composite cover. The metallic body may have a first side, a second side, a plurality of first retention slots, and a plurality of second retention slots, in accordance with various embodiments. The first and second retention slots may extend from the first side to the second side of the metallic body. The first composite cover may be coupled to the first side of the metallic body and may include a plurality of first fingers that extend through the first retention slots and are coupled to the second side of the metallic body. The second composite cover may be coupled to the second side of the metallic body and may include a plurality of second fingers that extend through the second retention slots and are coupled to the first side of the metallic body.
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公开(公告)号：US09650902B2
公开(公告)日：2017-05-16
申请号：US13739218
申请日：2013-01-11
Applicant: United Technologies Corporation
Inventor： Scott C. Billings , James O. Hansen , Michael A. Weisse
CPC classification number: F01D5/3007 , F01D5/3092 , F01D11/008 , F05D2220/36 , Y02T50/673
Abstract: A fan section for a gas turbine engine includes a fan hub having a slot. A platform is supported by the fan hub. A fan blade has a root that is received in the slot. A wear pad is provided between the fan hub and the root and includes a flap integral with the wear pad to provide a seal relative to the platform. A fan blade for a gas turbine engine includes an airfoil extending from a root. A wear pad is secured to the root and has a free end providing a flap canted toward the root.
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公开(公告)号：US20160024946A1
公开(公告)日：2016-01-28
申请号：US14800157
申请日：2015-07-15
Applicant: United Technologies Corporation
Inventor： Michael A. Weisse
CPC classification number: F01D5/3007 , F01D5/02 , F01D5/025 , F01D5/3092 , F05D2220/32 , F05D2220/36 , F05D2240/30 , F05D2260/30 , F05D2260/96 , F05D2300/431
Abstract: A blade for use in a gas turbine engine, the blade having an airfoil portion and a dovetail root portion, wherein the dovetail root portion is dimensioned and configured to enable the blade to rotate within a shaped slot formed in a supporting hub of the engine about a center of rotation that extends parallel to a central axis of the hub in response to an impact force on the airfoil portion of the blade.
Abstract translation: 一种用于燃气涡轮发动机的叶片，叶片具有翼型部分和燕尾根部分，其中燕尾根部的尺寸和构造使得叶片能够在形成于发动机的支撑轮毂内的成形槽内旋转， 响应于叶片的翼型部分上的冲击力而平行于毂的中心轴线延伸的旋转中心。
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Patent Agency Ranking
公开(公告)号：US20150110636A1
公开(公告)日：2015-04-23
申请号：US14170985
申请日：2014-02-03
Applicant: United Technologies Corporation
Inventor： Jay T. Abraham , Ethan C. Drew , Scott C. Billings , Michael A. Weisse , James O. Hansen , Venkatarama K. Seetharaman
CPC classification number: F01D5/3092 , F05D2220/36 , F05D2300/614 , F05D2300/701 , Y02T50/671
Abstract: A fan blade of a gas turbine engine includes an airfoil, a root received in a slot of a hub, and a wear pad covering at least a portion of the root and made of an integrally bonded woven composite laminate.
Abstract translation: 燃气涡轮发动机的风扇叶片包括翼型件，容纳在轮毂的槽中的根部和覆盖根部的至少一部分并由整体结合的织造复合层压板制成的耐磨垫片。
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公开(公告)号：US20140212261A1
公开(公告)日：2014-07-31
申请号：US13719859
申请日：2012-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Michael A. Weisse
CPC classification number: F04D29/326 , F01D5/225 , F01D11/02 , F02C3/107 , F04D27/004 , F04D27/0261 , F04D29/164 , F04D29/321 , F05D2220/36 , F05D2300/603 , Y02T50/673 , Y10T29/49229
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括除了别的以外的风扇部分，其包括具有可围绕轴线旋转的多个风扇叶片的风扇和罩，以及与风扇连通的变速装置。
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公开(公告)号：US10273816B2
公开(公告)日：2019-04-30
申请号：US14170985
申请日：2014-02-03
Applicant: United Technologies Corporation
Inventor： Jay T. Abraham , Ethan C. Drew , Scott C. Billings , Michael A. Weisse , James O. Hansen , Venkatarama K. Seetharaman
IPC: F01D5/30
Abstract: A fan blade of a gas turbine engine includes an airfoil, a root received in a slot of a hub, and a wear pad covering at least a portion of the root and made of an integrally bonded woven composite laminate.
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公开(公告)号：US09909429B2
公开(公告)日：2018-03-06
申请号：US14774895
申请日：2014-03-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James Cosby , Kwan Hui , Michael A. Weisse
CPC classification number: F01D5/3007 , F01D5/12 , F01D5/141 , F01D5/28 , F01D5/30 , F01D5/3023 , F01D5/303 , F01D5/3038 , F01D5/3053 , Y02T50/671 , Y02T50/673
Abstract: A blade for use in a gas turbine engine has an airfoil and a dovetail. The airfoil extends radially outwardly of the dovetail. An inner surface of the dovetail includes a slot extending along a length of the dovetail between a leading edge and a trailing edge. A rotor and a gas turbine engine are also disclose.
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公开(公告)号：US09453418B2
公开(公告)日：2016-09-27
申请号：US13716930
申请日：2012-12-17
Applicant: United Technologies Corporation
Inventor： Kwan Hui , Michael A. Weisse , Darin S. Lussier , Hillary Anne Huttenhower
CPC classification number: F01D5/147 , F01D5/282 , F05D2300/612 , Y02T50/672 , Y02T50/673 , Y10T156/1002 , Y10T428/12479 , Y10T428/13 , Y10T428/1366 , Y10T428/1376
Abstract: A hollow article includes a metallic hollow article formed from a having a first major surface, an internal cavity with an opening in the first major surface, and a socket around the opening; a cover of composite material received in the socket and covering the opening; and a filler material of foam in the internal cavity.
Abstract translation: 中空制品包括由第一主表面形成的金属中空制品，在第一主表面上具有开口的内腔和围绕开口的插座; 复合材料的盖子容纳在插座中并覆盖开口; 和在内腔中的泡沫填料。
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