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    Gas turbine engine, and fan blade and design method for the same
    2.
    发明专利
    Gas turbine engine, and fan blade and design method for the same 审中-公开
    气体涡轮发动机，风扇叶片及其设计方法

    公开(公告)号：JP2013096416A

    公开(公告)日：2013-05-20

    申请号：JP2012241532

    申请日：2012-11-01

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： MURDOCK JAMES R

    IPC: F02K3/06 ,  F01D25/00 ,  F02C7/00

    CPC classification number: F02K3/06 ,  F01D5/18 ,  F01D5/26 ,  F05D2260/94 ,  Y10T29/49339

    Abstract: PROBLEM TO BE SOLVED: To provide a fan blade that contains fillers 102, 104 respectively selected according to a problem occurring at specific positions in channels.SOLUTION: A fan blade 20 of a gas turbine engine comprises a body 28 extending between a leading edge 21 and a trailing edge 22. Channels 30 are formed in the body 28 while ribs 26 extend between the channels. The fan blade 20 contains a rigid material 102 and a damping material 104 that are arranged in the channels. The rigid material 102 is selected so as to impart further rigidity to the fan blade while the damping material 104 is selected so as to impart damping characteristics. A channel 101 is filled with the rigid material 102. A channel 103 has a part filled with the rigid material 102 and a part filled with the damping material 104 selected so as to have damping characteristics. A channel 41 contains the material 104 while a channel 300 does not contain the materials 102, 104.

    Abstract translation: 要解决的问题：提供一种风扇叶片，其包含分别根据在通道中的特定位置处发生的问题选择的填料102,104。 解决方案：燃气涡轮发动机的风扇叶片20包括在前缘21和后缘22之间延伸的主体28.通道30形成在主体28中，而肋26在通道之间延伸。 风扇叶片20包含布置在通道中的刚性材料102和阻尼材料104。 选择刚性材料102，以便在选择阻尼材料104以赋予阻尼特性时赋予风扇叶片更多的刚度。 通道101填充有刚性材料102.通道103具有填充有刚性材料102的部分和填充有被选择为具有阻尼特性的阻尼材料104的部分。 通道41包含材料104，而通道300不包含材料102,104。版权所有（C）2013，JPO＆INPIT

    ELECTRICAL GROUNDING FOR BLADE SHEATH
    3.
    发明申请
    ELECTRICAL GROUNDING FOR BLADE SHEATH 审中-公开
    叶片电气接地

    公开(公告)号：WO2014105224A3

    公开(公告)日：2014-09-18

    申请号：PCT/US2013057972

    申请日：2013-09-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MURDOCK JAMES R

    IPC: F01D5/14 ,  F02C7/20

    CPC classification number: F01D5/28 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2240/303 ,  F05D2300/121 ,  F05D2300/50 ,  Y02T50/671

    Abstract: A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first material. The first material is less electrically conductive than the second material. A grounding element is in contact with the sheath. The grounding element is in contact with a portion of the airfoil formed of a third material that is more electrically conductive than the first material. The grounding element and the portion of the airfoil together form a ground path from the sheath into the airfoil.

    Abstract translation: 用于燃气涡轮发动机的叶片具有包括前缘和后缘的翼型件。 护套定位在前缘，并通过由第一材料形成的第一粘合剂固定到翼型件上。 护套由与第一材料不同的第二材料形成。 第一材料比第二材料导电性差。 接地元件与护套接触。 接地元件与由比第一材料更导电的第三材料形成的翼型的一部分接触。 接地元件和翼型件的一部分一起形成从护套到翼型件的接地路径。

    FAN BLADE ATTACHMENT OF GAS TURBINE ENGINE
    4.
    发明申请
    FAN BLADE ATTACHMENT OF GAS TURBINE ENGINE 审中-公开
    气体涡轮发动机风机叶片附件

    公开(公告)号：WO2013158176A3

    公开(公告)日：2014-01-23

    申请号：PCT/US2013023155

    申请日：2013-01-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MURDOCK JAMES R ,  MCKAVENEY CHRISTOPHER S ,  ELLIOTT JASON

    IPC: B64C27/46 ,  B64C11/16 ,  B64C27/48

    CPC classification number: F01D5/3007 ,  F05D2220/36 ,  F05D2250/131 ,  F05D2250/14 ,  F05D2250/141

    Abstract: A fan blade includes a root including a front surface, a rear surface, a first side surface connected to the front surface and the rear surface, and a second side surface connected to the front surface and the rear surface. The front surface engages the first side surface and the second side surface by one or more blunted surfaces, and the rear surface engages the first side surface and the second side surface by one or more blunted surfaces. A blade extends from the root.

    Abstract translation: 风扇叶片包括根部，其包括前表面，后表面，连接到前表面和后表面的第一侧表面，以及连接到前表面和后表面的第二侧表面。 前表面通过一个或多个钝化表面接合第一侧表面和第二侧表面，并且后表面通过一个或多个钝化表面接合第一侧表面和第二侧表面。 刀片从根部延伸出来。

    HOLLOW FAN BLADE TUNING USING DISTINCT FILLER MATERIALS
    5.
    发明专利
    HOLLOW FAN BLADE TUNING USING DISTINCT FILLER MATERIALS 未知

    公开(公告)号：CA2794013A1

    公开(公告)日：2013-05-03

    申请号：CA2794013

    申请日：2012-10-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MURDOCK JAMES R

    IPC: F01D5/28 ,  F01D5/26

    Abstract: A fan blade comprises a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. Material is deposited within the channels, with one type of material being selected to provide additional stiffness to the fan blade, and a second type of material being selected for having good damping characteristics. A method and gas turbine engine are also disclosed.

    HOLLOW FAN BLADE TUNING USING DISTINCT FILLER MATERIALS
    9.
    发明专利
    HOLLOW FAN BLADE TUNING USING DISTINCT FILLER MATERIALS 未知

    公开(公告)号：CA2794013C

    公开(公告)日：2016-01-19

    申请号：CA2794013

    申请日：2012-10-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MURDOCK JAMES R

    IPC: F01D5/28 ,  F01D5/26

    Abstract: A fan blade comprises a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. Material is deposited within the channels, with one type of material being selected to provide additional stiffness to the fan blade, and a second type of material being selected for having good damping characteristics. A method and gas turbine engine are also disclosed.

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