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    METHOD AND DEVICE FOR REPLACING VANE ASSEMBLY OF TURBINE ENGINE
    1.
    发明专利
    METHOD AND DEVICE FOR REPLACING VANE ASSEMBLY OF TURBINE ENGINE 失效

    公开(公告)号：JPH1054207A

    公开(公告)日：1998-02-24

    申请号：JP14891497

    申请日：1997-06-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DEAL JAMES L ,  LAMM FOSTER P ,  MORENO GUSTAVO

    IPC: F01D25/00 ,  F01D5/00 ,  F01D5/30 ,  F01D9/04 ,  F04D29/32

    Abstract: PROBLEM TO BE SOLVED: To provide a swift and simple method and a related device for replacing a damaged vane assembly located at a rear of the fan of a turbine engine. SOLUTION: A repair device for replacing a vane which cannot be used by a turbine engine has a vane sub-assembly which is provided with an air foil 124 attached with a base connected to a base end part and an opposite base 1 which can be slided on the air foil which can be used. The opposite base 156 is slide toward a connection base through an end part of the air foil 134. The opposite base 156 is fixed to an outside easing with a stud and a nut.

    HYBRID METAL FAN BLADE
    2.
    发明申请
    HYBRID METAL FAN BLADE 审中-公开
    混合金属风扇叶片

    公开(公告)号：WO2014196987A3

    公开(公告)日：2015-02-26

    申请号：PCT/US2013046819

    申请日：2013-06-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DEAL JAMES L ,  SCHIRRA JOHN J ,  DROZDENKO LEE ,  GRAVES WILLIAM R ,  HANSEN JAMES O ,  WEISSE MICHAEL A ,  WATSON THOMAS J

    IPC: F01D5/14 ,  F01D5/28 ,  F04D29/38

    CPC classification number: F01D5/288 ,  F01D5/147 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2240/303 ,  F05D2300/121 ,  F05D2300/124 ,  F05D2300/174 ,  Y02T50/672

    Abstract: A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt% and about 3.0 wt% of lithium.

    Abstract translation: 风扇叶片包括翼型部分和鞘部分。 护套部分具有鞘头部分，第一护套侧面和第二护套侧面，两个侧面从前鞘部分向翼伸出。 护套部分结合到翼型部分，使得鞘头部分覆盖前翼型边缘，限定叶片前缘。 第一护套侧面覆盖靠近翼型件前缘的第一翼型件表面的一部分，共同限定叶片抽吸表面。 第二护套侧面覆盖靠近翼型件前缘的第二翼型件表面的一部分，共同限定叶片压力表面。 第一种金属材料是含有约0.5wt％至约3.0wt％的锂的铝合金。

    3.
    发明专利
    未知

    公开(公告)号：DE69721853T2

    公开(公告)日：2004-05-06

    申请号：DE69721853

    申请日：1997-06-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DEAL JAMES L ,  LAMM FORSTER P ,  MORENO GUSTAVO

    IPC: F01D25/00 ,  F01D5/00 ,  F01D5/30 ,  F01D9/04 ,  F04D29/32 ,  F04D29/34

    Abstract: A repair kit for replacing an unserviceable vane assembly in a turbine engine includes a serviceable vane subassembly (120) having a serviceable airfoil (124) with a base (134) attached to the root end thereof and an opposing base (156) which is unattached to but slidably engagable with the serviceable airfoil. The opposing base is slipped over the tip end of the airfoil and slid toward the opposing base. The vane subassembly and opposing base are pivoted into position between inner and outer engine cases in place of an unserviceable vane assembly so that receptor sockets (148, 150) in the attached base engage support pins (72) extending from the inner case. An adhesive (182) is applied to the tip end of the serviceable airfoil and the opposing base is translated into its installed position near the tip end of the airfoil. Upon curing of the adhesive, the opposing base becomes attached to the airfoil. The base is secured to the outer case by studs (196) and nuts (198).

    4.
    发明专利
    未知

    公开(公告)号：DE69721853D1

    公开(公告)日：2003-06-12

    申请号：DE69721853

    申请日：1997-06-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DEAL JAMES L ,  LAMM FORSTER P ,  MORENO GUSTAVO

    IPC: F01D25/00 ,  F01D5/00 ,  F01D5/30 ,  F01D9/04 ,  F04D29/32 ,  F04D29/34

    Abstract: A repair kit for replacing an unserviceable vane assembly in a turbine engine includes a serviceable vane subassembly (120) having a serviceable airfoil (124) with a base (134) attached to the root end thereof and an opposing base (156) which is unattached to but slidably engagable with the serviceable airfoil. The opposing base is slipped over the tip end of the airfoil and slid toward the opposing base. The vane subassembly and opposing base are pivoted into position between inner and outer engine cases in place of an unserviceable vane assembly so that receptor sockets (148, 150) in the attached base engage support pins (72) extending from the inner case. An adhesive (182) is applied to the tip end of the serviceable airfoil and the opposing base is translated into its installed position near the tip end of the airfoil. Upon curing of the adhesive, the opposing base becomes attached to the airfoil. The base is secured to the outer case by studs (196) and nuts (198).

    HYBRID METAL FAN BLADE
    6.
    发明专利
    HYBRID METAL FAN BLADE 未知

    公开(公告)号：SG173944A1

    公开(公告)日：2011-09-29

    申请号：SG2010089142

    申请日：2010-12-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DEAL JAMES L ,  SCHIRRA JOHN J ,  DROZDENKO LEE ,  GRAVES WILLIAM R ,  HANSEN JAMES O

    Abstract: A fan blade is disclosed comprising a lightweight metallic airfoil portion and a high-strength sheath portion. The airfoil portion has a forward airfoil edge, a first airfoil surface, and a second airfoil surface. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface.Fig 2.

    HOLLOW FAN BLADE
    8.
    发明专利
    HOLLOW FAN BLADE 未知

    公开(公告)号：SG173949A1

    公开(公告)日：2011-09-29

    申请号：SG2010093862

    申请日：2010-12-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DEAL JAMES L ,  GRAVES WILLIAM R ,  WEISSE MICHAEL A

    Abstract: A blade includes a hollow metal airfoil having an opening to an internal cavity in a first major surface. A metal cover is adhesively bonded to a socket formed around the opening. The cover encloses the cavity and provides a continuous first major surface.(Figure 3B)

    9.
    发明专利
    未知

    公开(公告)号：AT158213T

    公开(公告)日：1997-10-15

    申请号：AT93908647

    申请日：1993-03-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DEAL JAMES L ,  GOSSELIN JOSEPH A ,  KOLESNIK JOHN J

    IPC: B23B31/16 ,  B23K20/12

    Abstract: A workpiece location and support means as described which is free from any tendency to locate the workpiece in a predetermined position. The workpiece is supported and located by a series of hydraulic actuators which in one condition permit the workpiece to move freely but in another hydraulic condition lock the workpiece in one place and do not permit motion thereof. The present invention has particular application as a workpiece support in inertia bonding machines.

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