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    METHOD OF MANUFACTURING A COMPOSITE STRUCTURE AND COMPOSITE STRUCTURE OBTAINED THEREBY
    72.
    发明申请
    METHOD OF MANUFACTURING A COMPOSITE STRUCTURE AND COMPOSITE STRUCTURE OBTAINED THEREBY 有权
    制造复合结构的方法和获得的复合结构

    公开(公告)号：US20130199718A1

    公开(公告)日：2013-08-08

    申请号：US13878492

    申请日：2011-10-11

    申请人： Benjamin Ralfs ,  John Moram

    发明人： Benjamin Ralfs ,  John Moram

    IPC分类号： B32B37/18 ,  B32B38/00

    CPC分类号： B32B37/18 ,  B29C33/0011 ,  B29C33/20 ,  B29C33/485 ,  B29C70/382 ,  B29C70/386 ,  B29C70/54 ,  B29L2031/7504 ,  B32B38/0004 ,  Y10T156/108

    摘要： An example of a composite structure is a containment case 2 for a gas turbine engine 1 which comprises an annular housing 3 and an annular flange 4 which is integral with and is positioned at an end of the housing 3. The housing 3 comprises composite material which includes tape 9 laid in the circumferential direction of the housing. The flange 4 comprises composite material which includes tape 8 laid at an oblique angle to the circumferential direction of the flange 4 and/or tape 7 laid at a perpendicular angle to the circumferential direction. The flange 4 does not include tape 9 laid in the circumferential direction of the flange, because such tape would impede the forming of the flange material to form the flange.

    摘要翻译： 复合结构的实例是用于燃气涡轮发动机1的容纳壳体2，其包括环形壳体3和与壳体3一体并位于壳体3的一端的环形凸缘4.壳体3包括复合材料， 包括沿壳体的圆周方向放置的带9。 凸缘4包括复合材料，其包括以与凸缘4的圆周方向倾斜的角度放置的带8和/或以与圆周方向垂直的角度放置的带7。 凸缘4不包括沿凸缘的圆周方向铺设的带9，因为这种带会妨碍凸缘材料的形成以形成凸缘。

    Wind turbine blades made of two separate sections, and method of assembly
    76.
    发明授权
    Wind turbine blades made of two separate sections, and method of assembly 有权
    风力涡轮机叶片由两个独立的部分组成，以及组装方法

    公开(公告)号：US08348622B2

    公开(公告)日：2013-01-08

    申请号：US11629795

    申请日：2004-06-30

    申请人： Anton Bech

    发明人： Anton Bech

    IPC分类号： F03D1/06 ,  F01D5/14

    CPC分类号： B29C66/721 ,  B29C65/4815 ,  B29C65/483 ,  B29C66/1142 ,  B29C66/1162 ,  B29C66/223 ,  B29C66/54 ,  B29C66/71 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/7254 ,  B29C66/9121 ,  B29C66/9141 ,  B29C66/9161 ,  B29C66/9534 ,  B29C66/961 ,  B29K2105/101 ,  B29K2307/00 ,  B29K2309/08 ,  B29L2031/08 ,  B29L2031/085 ,  B29L2031/7504 ,  F03D1/0675 ,  F05B2230/23 ,  F05B2240/302 ,  Y02E10/721 ,  Y02P70/523 ,  Y10T29/49336 ,  B29K2063/00 ,  B29K2307/04

    摘要： The invention relates to a wind turbine blade comprising at least two wind turbine blade sections that include one or more strengthening structures, the ends of the strengthening structures being connected in a connection joint. The ends include corresponding connection surfaces, the one or more relevant dimensions of the surfaces being larger than the dimensions of the transverse surfaces of the strengthening structures at the ends. The one or more relevant dimensions of the connection joint are larger than that of the adjacent strengthening structure. The invention also relates to a wind turbine blade in which the at least two wind turbine blade sections include a number of substantially oblong carbon fiber strips and strips of one or further materials such as wood or glass fiber. The invention further relates to a wind turbine blade section, an assembly plant for assembling wind turbine blade sections and to a method and use of such wind turbine blades.

    摘要翻译： 本发明涉及一种包括至少两个包括一个或多个强化结构的风力涡轮机叶片部分的风力涡轮机叶片，加强结构的端部以连接接头连接。 端部包括相应的连接表面，表面的一个或多个相关尺寸大于端部处的加强结构的横向表面的尺寸。 连接接头的一个或多个相关尺寸大于相邻加强结构的尺寸。 本发明还涉及一种风力涡轮机叶片，其中所述至少两个风力涡轮机叶片部分包括若干基本上椭圆形的碳纤维条和一种或多种材料的条，例如木材或玻璃纤维。 本发明还涉及风力涡轮机叶片部分，用于组装风力涡轮机叶片部分的组装设备以及这种风力涡轮机叶片的方法和用途。

    FAN CASE CONTAINMENT SYSTEM AND METHOD OF FABRICATION
    77.
    发明申请
    FAN CASE CONTAINMENT SYSTEM AND METHOD OF FABRICATION 有权
    风扇装置系统和制造方法

    公开(公告)号：US20120034076A1

    公开(公告)日：2012-02-09

    申请号：US13196502

    申请日：2011-08-02

    申请人： Ming Xie

    发明人： Ming Xie

    IPC分类号： F01D25/24 ,  B65H81/02

    CPC分类号： F01D21/045 ,  B29C70/32 ,  B29D99/0014 ,  B29L2031/7504 ,  Y02T50/672 ,  Y10T428/13 ,  Y10T428/24149

    摘要： Composite article includes a generally cylindrical body having an internal grid structure interleaved with casing layers formed of reinforcing fibers disposed in a resin matrix. The composite article may be utilized in a fan case containment system for aircraft engine applications. Methods for fabricating the composite article are also provided.

    摘要翻译： 复合制品包括具有内部格栅结构的大致圆柱形主体，该内部格栅结构与设置在树脂矩阵中的增强纤维形成的外壳层交错。 复合制品可用于用于飞机发动机应用的风扇壳体容纳系统。 还提供了制造复合制品的方法。

    Methods and apparatus for assembling composite structures
    78.
    发明授权
    Methods and apparatus for assembling composite structures 有权
    复合结构组装方法与装置

    公开(公告)号：US08079773B2

    公开(公告)日：2011-12-20

    申请号：US11252951

    申请日：2005-10-18

    申请人： Lee Alan Blanton

    发明人： Lee Alan Blanton

    IPC分类号： F16L23/00

    CPC分类号： F01D25/243 ,  B29C65/562 ,  B29C66/1312 ,  B29C66/54 ,  B29C66/721 ,  B29L2031/7504 ,  F05D2300/603 ,  F16B2200/50 ,  F16B2200/506 ,  F16B2200/509 ,  F16L23/032 ,  F16L47/14 ,  F16L47/24 ,  Y10T29/49236 ,  Y10T403/27

    摘要： A method facilitates assembling a turbine engine casing. A first casing section is positioned radially outward from a turbine engine. The first casing includes a first flange having an outer end portion, an inner end portion, and a body therebetween. At least a portion of the outer end portion has a partial frusto-conical cross-sectional profile. A second casing section including a second flange is positioned adjacent the first casing section such that a mating surface of the second flange is positioned substantially flush against a first flange mating surface. Each respective mating surface is opposite a respective load-bearing surface. A fastener is inserted through an opening in the first and second flanges to couple casing sections together such that a portion of a load-bearing surface extending over the first flange outer end portion facilitates distributing loading induced therein substantially equally across the load bearing surface.

    摘要翻译： 一种方法有利于组装涡轮发动机外壳。 第一壳体部分从涡轮发动机径向向外定位。 第一壳体包括具有外端部分，内端部分和与其之间的主体的第一凸缘。 外端部的至少一部分具有局部截头圆锥形截面轮廓。 包括第二凸缘的第二壳体部分定位成与第一壳体部分相邻，使得第二凸缘的配合表面基本上与第一凸缘配合表面齐平。 每个相应的配合表面与相应的承载表面相对。 紧固件插入通过第一和第二凸缘中的开口，以将壳体部分联接在一起，使得在第一凸缘外端部分上延伸的承载表面的一部分有助于在其中基本上均匀地分布载荷承载表面上的载荷。

    Composite fan containment case and methods of fabricating the same
    80.
    发明授权
    Composite fan containment case and methods of fabricating the same 有权
    复合风扇收容箱及其制造方法

    公开(公告)号：US08021102B2

    公开(公告)日：2011-09-20

    申请号：US11565347

    申请日：2006-11-30

    申请人： Ming Xie ,  Michael Scott Braley

    发明人： Ming Xie ,  Michael Scott Braley

    IPC分类号： F01D25/24

    CPC分类号： B29C70/32 ,  B29C70/086 ,  B29L2031/7504 ,  Y10T29/4932

    摘要： A method of fabricating a fan containment case for a gas turbine engine is provided. The method includes forming a core layer material, wrapping the core layer material about a cylindrically-shaped take-up spool, and transferring the core layer material to a cylindrically-shaped mandrel by wrapping a plurality of layers of the core layer material about the mandrel such that the mandrel is circumscribed by the layers and such that a size and a cylindrical shape of the fan containment case are defined by the layers of core layer material.

    摘要翻译： 提供一种制造用于燃气涡轮发动机的风扇容纳箱的方法。 该方法包括形成芯层材料，将芯层材料围绕圆柱形卷取卷轴缠绕，并且通过将多层芯层材料围绕心轴缠绕而将芯层材料转移到圆柱形心轴 使得心轴被层限制，并且使得风扇容纳壳体的尺寸和圆柱形形状由芯层材料层限定。