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14 条记录 (耗时 0.012 秒)

    VANE LINKING PORTION STRUCTURE, AND JET ENGINE USING SAME
    1.
    发明授权
    VANE LINKING PORTION STRUCTURE, AND JET ENGINE USING SAME 有权

    公开(公告)号：EP2865879B1

    公开(公告)日：2018-10-31

    申请号：EP13806092.6

    申请日：2013-06-19

    申请人： IHI Corporation ,  IHI Aerospace Co., Ltd.

    发明人： INADA, Takaomi ,  TANAKA, Shinichi

    IPC分类号： F02K3/06 ,  F01D9/02 ,  F01D25/24 ,  F02C7/00 ,  F01D25/00 ,  F01D5/28

    CPC分类号： F01D25/005 ,  F01D5/282 ,  F01D9/02 ,  F01D25/24 ,  F05D2230/644 ,  F05D2240/12 ,  F05D2260/31 ,  F05D2300/44 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

    摘要： A coupling support member 33 including a pair of divided pieces 34, 34 is placed in a coupling part between a vane proximal end portion 21 of a guide vane 20 and an attachment flange 31f, and the pair of divided pieces 34, 34 are joined to the vane proximal end portion 21 from both the sides in the vane thickness direction. A groove 35b is formed in one end portion joint surface 35a of the coupling support member 33, a linear protrusion 35c is formed on the other end portion joint surface 35a, the vane proximal end portion 21 is formed into a concavo-convex shape, a linear protrusion 21b that is engaged with the groove 35b which is formed in the end portion joint surface 35a is formed on a joint surface 21a to the one end portion joint surface 35a, a groove 21c that is engaged with the linear protrusion 35c formed on the end portion joint surface 35a is formed in the joint surface 21a to the other end portion joint surface 35a. The vane proximal end portion 21 is held between the pair of divided pieces 34, 34 of the coupling support member 33, by the fastening force that is applied to the coupling support member 33 from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine.

    VANE LINKING PORTION STRUCTURE, AND JET ENGINE USING SAME
    2.
    发明公开
    VANE LINKING PORTION STRUCTURE, AND JET ENGINE USING SAME 审中-公开
    SCHAUFELVERBINDUNGSABSCHNITTSTRUKTUR UND STRAHLTRIEBWERK DAMIT

    公开(公告)号：EP2865879A1

    公开(公告)日：2015-04-29

    申请号：EP13806092.6

    申请日：2013-06-19

    申请人： IHI Corporation ,  IHI Aerospace Co., Ltd.

    发明人： INADA, Takaomi ,  TANAKA, Shinichi

    IPC分类号： F02K3/06 ,  F01D9/02 ,  F01D25/24 ,  F02C7/00

    CPC分类号： F01D25/005 ,  F01D5/282 ,  F01D9/02 ,  F01D25/24 ,  F05D2230/644 ,  F05D2240/12 ,  F05D2260/31 ,  F05D2300/44 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

    摘要： A coupling support member 33 including a pair of divided pieces 34, 34 is placed in a coupling part between a vane proximal end portion 21 of a guide vane 20 and an attachment flange 31f, and the pair of divided pieces 34, 34 are joined to the vane proximal end portion 21 from both the sides in the vane thickness direction. A groove 35b is formed in one end portion joint surface 35a of the coupling support member 33, a linear protrusion 35c is formed on the other end portion joint surface 35a, the vane proximal end portion 21 is formed into a concavo-convex shape, a linear protrusion 21b that is engaged with the groove 35b which is formed in the end portion joint surface 35a is formed on a joint surface 21a to the one end portion joint surface 35a, a groove 21c that is engaged with the linear protrusion 35c formed on the end portion joint surface 35a is formed in the joint surface 21a to the other end portion joint surface 35a. The vane proximal end portion 21 is held between the pair of divided pieces 34, 34 of the coupling support member 33, by the fastening force that is applied to the coupling support member 33 from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine.

    摘要翻译： 包括一对分割片34,34的联接支撑构件33被放置在导向叶片20的叶片近端部分21和安装凸缘31f之间的联接部分中，并且一对分割片34,34与 叶片近端部21从叶片厚度方向的两侧。 在联接支撑构件33的一个端部接合面35a上形成有槽35b，在另一端部接合面35a上形成有直线状突起35c，叶片基端部21形成为凹凸状， 与形成在端部接合面35a中的槽35b接合的直线状突起21b形成在与一端部接合面35a的接合面21a上，与形成在该端部接合面35a上的直线突起35c接合的槽21c 端部接合表面35a形成在另一端部接合表面35a的接合表面21a中。 叶片近端部21通过从叶片厚度方向的两侧施加到联接支撑构件33的紧固力而保持在联接支撑构件33的一对分割片34,34之间。 可以获得高的结构强度，同时有助于减少喷气发动机的重量。

    METHOD AND DEVICE FOR MANUFACTURING FAN BLADE
    4.
    发明公开
    METHOD AND DEVICE FOR MANUFACTURING FAN BLADE 有权
    VERFAHREN UND VORRICHTUNG ZUR HERSTELLUNG VON EINERBLÄSERSCHAUFEL

    公开(公告)号：EP2957775A1

    公开(公告)日：2015-12-23

    申请号：EP14752187.6

    申请日：2014-02-13

    申请人： IHI Corporation ,  IHI Aerospace Co., Ltd.

    发明人： INADA, Takaomi ,  MORITA, Hideo ,  YAGI, Hiroyuki ,  MURAKAMI, Tsutomu ,  TANAKA, Shinichi

    IPC分类号： F04D29/38 ,  B29C70/06 ,  F01D5/28 ,  B29K105/08 ,  B29L31/08 ,  B29L31/30

    CPC分类号： B29C51/00 ,  B29C70/46 ,  B29C70/56 ,  B29D99/0025 ,  B29L2031/08 ,  B29L2031/082 ,  F01D5/282 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2230/20 ,  F05D2230/40 ,  F05D2300/44 ,  F05D2300/603

    摘要： A blank sheet (7) including a plurality of main fibers (71) arranged in parallel with each other, auxiliary fibers (72) and a resin that consolidates the fibers is heated to a temperature at which the resin softens, and then pressed against a fan blade mold (6b) with the direction of the main fibers (71) aligned with the longitudinal direction of the fan blade mold (6b). The fan blade mold (6b) is shaped so that the length thereof in the longitudinal direction along the surface of a center part (64x) thereof in the width direction is shorter than the length thereof in the longitudinal direction along the surface of end parts (64y) thereof in the width direction. When the blank sheet (7) is pressed against the fan blade mold (6b), a center part (7x) in the width direction of the blank sheet (7) at an end part (7a) in the longitudinal direction is pulled with a greater force than end parts (7y) in the width direction of the blank sheet (7) at the end part (7a) in the longitudinal direction, thereby preventing occurrence of wrinkling.

    摘要翻译： 包括彼此平行布置的多个主纤维（71）的辅助纤维（72）和固定纤维的树脂的空白片材（7）被加热到树脂软化的温度，然后压在 风扇叶片模具（6b）与主纤维（71）的方向与风扇叶片模具（6b）的纵向对准。 风扇叶片模具（6b）的形状使得其沿宽度方向的中心部（64x）的表面的长度方向的长度比沿端部的表面的长度方向的长度短 64y）。 当坯料（7）被压靠在风扇叶片模具（6b）上时，沿着纵向方向在端部（7a）处沿着坯料（7）的宽度方向的中心部分（7x）被拉 在长度方向上在端部（7a）处的坯料（7）的宽度方向上的端部（7y）的力大，从而防止起皱。

    VANE COUPLING PART STRUCTURE AND JET ENGINE USING SAME
    6.
    发明公开
    VANE COUPLING PART STRUCTURE AND JET ENGINE USING SAME 有权
    SCHAUFELKUPPLUNGSTEILSTRUKTUR UND STRAHLTRIEBWERK DAMIT

    公开(公告)号：EP2811138A1

    公开(公告)日：2014-12-10

    申请号：EP13743758.8

    申请日：2013-02-01

    申请人： IHI Corporation

    发明人： YAGI, Hiroyuki ,  ISHIGURE, Tadahiro ,  INADA, Takaomi ,  MUROOKA, Takeshi ,  MORITA, Hideo ,  HONDA, Tatsuhito

    IPC分类号： F02C7/20 ,  F01D9/02 ,  F01D25/24 ,  F02C7/00 ,  F02K3/06 ,  F04D29/54

    CPC分类号： F01D9/042 ,  F01D5/282 ,  F01D25/162 ,  F01D25/246 ,  F02C7/20 ,  F05D2260/31 ,  F05D2260/36 ,  Y02T50/672 ,  Y02T50/673

    摘要： A coupling support member 33 including a pair of divided pieces 34, 34 is placed in a coupling part between a vane proximal end portion 21 of a guide vane 20 and an attachment flange 31f, and the pair of divided pieces 34, 34 are joined to the vane proximal end portion 21 from both the sides in the vane thickness direction. A linear protrusion 21b is formed on one of joint surfaces 21a, 21a of the vane proximal end portion 21 to the pair of divided pieces 34, 34. A groove 35b engaged with the linear protrusion 21b formed in the vane proximal end portion 21 is formed on one of respective joint surfaces 35a, 35a of the pair of divided pieces 34, 34 of the coupling support member 33. The vane proximal end portion 21 is held between the pair of divided pieces 34, 34 of the coupling support member 33, by the fastening force that is applied to the pair of divided pieces 34, 34 of the coupling support member 33 from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine.

    摘要翻译： 包括一对分割片34,34的联接支撑构件33被放置在导向叶片20的叶片近端部分21和安装凸缘31f之间的联接部分中，并且一对分割片34,34与 叶片近端部21从叶片厚度方向的两侧。 在叶片基端部21的一个接合面21a，21a上形成有线状的突起部21b，形成在与叶片基端部21形成的直线突起21b嵌合的槽35b 在联接支撑构件33的一对分割片34,34的各个接合表面35a，35a中的一个上。叶片近端部分21通过联接支撑构件33的一对分割片34,34之间被保持在 紧固力从叶片厚度方向的两侧施加到联接支撑构件33的一对分割片34,34。 可以获得高的结构强度，同时有助于减少喷气发动机的重量。

    ELECTROCONDUCTIVE STRUCTURE FOR JET ENGINE
    10.
    发明公开
    ELECTROCONDUCTIVE STRUCTURE FOR JET ENGINE 审中-公开
    导电结构体用于发动机

    公开(公告)号：EP3048257A1

    公开(公告)日：2016-07-27

    申请号：EP14845967.0

    申请日：2014-07-22

    申请人： IHI Corporation

    发明人： OBUCHI, Kenro ,  YAGI, Hiroyuki ,  FURUKAWA, Hiroyuki ,  MORITA, Hideo ,  INADA, Takaomi

    IPC分类号： F01D9/02 ,  F02C7/00 ,  F04D29/54

    摘要： An electric conduction structure for conducting and diverting electric current from a vane main body of an outlet guide vane into an exterior support structure is comprised of: a sheath of a metal covering a leading edge of the vane main body; and an electrically conductive pad of the metal comprising a contact portion so dimensioned as to have an overlap with an end of the sheath, and a washer portion into which a bolt for being tightened into the support structure is insertable, wherein one or more joints selected from the group of a weld, a spot-weld, a solder, a bond by an electrically conductive paste and a crimp establish connection between the end of the sheath and the contact portion.