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公开(公告)号：US20160017713A1
公开(公告)日：2016-01-21
申请号：US14772192
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James O. Hansen
CPC classification number: F01D5/02 , B22F5/04 , B22F7/08 , B23K20/002 , B23K20/02 , B23K31/02 , C22C1/0458 , C22C14/00 , C22C32/0073 , F01D5/282 , F01D5/30 , F01D5/34 , F01D25/24 , F05D2220/32 , F05D2240/20 , F05D2300/133 , F05D2300/174 , F05D2300/603 , F05D2300/702
Abstract: A turbine engine rotor component has a Ti-based first member (66) circumscribing an axis (500) and has either a circumferential array of integrally formed airfoils (62) or a circumferential array of blade retention features. A TiB particulate reinforced second member (90) also circumscribes the axis.
Abstract translation: 涡轮发动机转子部件具有围绕轴线（500）的Ti基第一部件（66），并且具有一体形成的翼型件（62）的圆周阵列或刀片保持部件的圆周阵列。 TiB颗粒增强的第二构件（90）也围绕轴线。
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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：US20180274120A1
公开(公告)日：2018-09-27
申请号：US15988109
申请日：2018-05-24
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , James O. Hansen
CPC classification number: C25D11/16 , C25D11/022 , C25D11/18 , C25D11/24 , F01D5/02 , F01D5/20 , F01D5/286 , F01D5/288 , F01D25/24 , F05D2220/32 , F05D2230/31 , F05D2230/90 , F05D2240/307 , F05D2240/31 , F05D2250/61 , F05D2300/121 , F05D2300/2112 , F05D2300/506
Abstract: A method is provided for manufacturing a blade. The blade comprises an airfoil (100) having: a root end and a tip (106); a metallic substrate (102) along at least a portion of the airfoil; and an anodized layer (154). The method comprises roughening the tip to form protrusions(158′; 402′) and anodizing to form the anodized layer so that the protrusions form an abrasive (156; 400).
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公开(公告)号：US10081082B2
公开(公告)日：2018-09-25
申请号：US14768633
申请日：2013-12-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James O. Hansen , David Ulrich Furrer
CPC classification number: B23P15/04 , B21D53/78 , B21H7/00 , B21K3/04 , F01D5/288 , F04D29/324 , F05D2220/32 , F05D2230/20 , F05D2240/303
Abstract: A method for manufacturing a protective sheath for a fan blade leading edge is described. The method may comprise generating a preform plate from a stock plate wherein the preform plate has a flattened surface and an inclined surface having a spike flanked by a first side and a second side. The method may further comprise bending the first side and the second side away from the spike to generate a sheath intermediate followed by generating the protective sheath from the sheath intermediate by shaping an outer surface and an inner surface of the sheath intermediate to match the contour of the fan blade leading edge.
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公开(公告)号：US20170198590A1
公开(公告)日：2017-07-13
申请号：US14992672
申请日：2016-01-11
Applicant: United Technologies Corporation
Inventor： Jesse C. Meyer , Joseph Jalowka , John D. Riehl , Raymond P. Martina , James O. Hansen
CPC classification number: F01D5/282 , B32B15/043 , B32B2255/06 , B32B2255/26 , B32B2603/00 , C09J5/02 , C09J5/04 , C09J5/06 , C09J2201/36 , C09J2463/00 , C22C21/00 , F05D2300/603
Abstract: The present disclosure provides methods and systems for the bonding of dissimilar substrates. For example, a first substrate may be coupled to a second substrate by a composite joint between the first substrate and the second substrate. The composite joint may be comprised of a first adhesive material and a second adhesive material. The first adhesive material may be disposed on the first substrate, and the second adhesive material may be disposed to the first adhesive material. The composite joint between the first substrate and the second substrate may provide an isolation layer therebetween, preventing galvanic corrosion.
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Patent Agency Ranking
公开(公告)号：US10472729B2
公开(公告)日：2019-11-12
申请号：US15988109
申请日：2018-05-24
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , James O. Hansen
Abstract: A method is provided for manufacturing a blade. The blade comprises an airfoil (100) having: a root end and a tip (106); a metallic substrate (102) along at least a portion of the airfoil; and an anodized layer (154). The method comprises roughening the tip to form protrusions (158′; 402′) and anodizing to form the anodized layer so that the protrusions form an abrasive (156; 400).
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公开(公告)号：US10364677B2
公开(公告)日：2019-07-30
申请号：US14772192
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： James O. Hansen
IPC: F01D5/02 , B22F5/04 , C22C14/00 , F01D5/34 , B22F7/08 , C22C1/04 , B23K20/00 , B23K20/02 , B23K31/02 , F01D5/28 , F01D5/30 , F01D25/24 , C22C32/00
Abstract: A turbine engine rotor component has a Ti-based first member (66) circumscribing an axis (500) and has either a circumferential array of integrally formed airfoils (62) or a circumferential array of blade retention features. A TiB particulate reinforced second member (90) also circumscribes the axis.
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公开(公告)号：US10221700B2
公开(公告)日：2019-03-05
申请号：US14992672
申请日：2016-01-11
Applicant: United Technologies Corporation
Inventor： Jesse C. Meyer , Joseph Jalowka , John D. Riehl , Raymond P. Martina , James O. Hansen
Abstract: The present disclosure provides methods and systems for the bonding of dissimilar substrates. For example, a first substrate may be coupled to a second substrate by a composite joint between the first substrate and the second substrate. The composite joint may be comprised of a first adhesive material and a second adhesive material. The first adhesive material may be disposed on the first substrate, and the second adhesive material may be disposed to the first adhesive material. The composite joint between the first substrate and the second substrate may provide an isolation layer therebetween, preventing galvanic corrosion.
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公开(公告)号：US09982358B2
公开(公告)日：2018-05-29
申请号：US14729534
申请日：2015-06-03
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , James O. Hansen
CPC classification number: C25D11/16 , C25D11/022 , C25D11/18 , C25D11/24 , F01D5/02 , F01D5/20 , F01D5/286 , F01D5/288 , F01D25/24 , F05D2220/32 , F05D2230/31 , F05D2230/90 , F05D2240/307 , F05D2240/31 , F05D2250/61 , F05D2300/121 , F05D2300/2112 , F05D2300/506
Abstract: A method is provided for manufacturing a blade. The blade comprises an airfoil (100) having: a root end and a tip (106); a metallic substrate (102) along at least a portion of the airfoil; and an anodized layer (154). The method comprises roughening the tip to form protrusions (158′; 402′) and anodizing to form the anodized layer so that the protrusions form an abrasive (156; 400).
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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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