利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

35 条记录 (耗时 0.031 秒)

    Method for producing a metal insert to protect a leading edge made of a composite material
    17.
    发明授权
    Method for producing a metal insert to protect a leading edge made of a composite material 有权
    用于制造金属插入件以保护由复合材料制成的前缘的方法

    公开(公告)号：US08782887B2

    公开(公告)日：2014-07-22

    申请号：US13635502

    申请日：2011-03-18

    申请人： Jean-Michel Patrick Maurice Franchet ,  Gilles Charles Casimir Klein

    发明人： Jean-Michel Patrick Maurice Franchet ,  Gilles Charles Casimir Klein

    IPC分类号： B21K3/04 ,  B23P15/04

    CPC分类号： B23P15/04 ,  B21D53/78 ,  B23K20/021 ,  B23K2101/001 ,  F01D5/147 ,  F01D5/282 ,  F04D29/324 ,  F05D2230/236 ,  F05D2230/50 ,  F05D2230/60 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49336 ,  Y10T29/49337

    摘要： A method for producing a metal insert for protecting a leading or trailing edge of a compressor vane of an aeronautical machine made of a composite material, by stamping sheets and diffusion bonding between the sheets. The method includes: initially shaping the sheets by stamping to approximate the sheets to a shape of a suction side and pressure side of the insert; producing a core shaped inner cavity of the metal insert to be manufactured, one of the surfaces thereof reproducing an inner shape of the suction side of the insert and the other surface reproducing an inner shape of the pressure side of the insert; positioning the sheets around the core and securing the assembly; applying a vacuum and sealing the assembly by bonding; assembling the assembly by hot isostatic compression; cutting the assembly to extract the core and separate the insert; producing an outer profile of the insert by a final machining.

    摘要翻译： 一种用于制造用于保护由复合材料制成的航空机械的压缩机叶片的前缘或后缘的金属插入件的方法，通过冲压片材和片材之间的扩散接合。 该方法包括：首先通过冲压来成形片材以将片材近似为插入物的吸力侧和压力侧的形状; 制造要制造的金属插入件的芯形内腔，其中一个表面再现插入件的吸入侧的内部形状，而另一个表面再现插入件的压力侧的内部形状; 将片材定位在芯部周围并固定组件; 施加真空并通过粘合密封组件; 通过热等静压压装配组件; 切割组件以提取芯部并分离插入件; 通过最终加工产生插入件的外部轮廓。

    METHOD FOR PRODUCING A METAL INSERT TO PROTECT A LEADING EDGE MADE OF A COMPOSITE MATERIAL
    18.
    发明申请
    METHOD FOR PRODUCING A METAL INSERT TO PROTECT A LEADING EDGE MADE OF A COMPOSITE MATERIAL 有权
    用于生产金属插件以保护复合材料的引导边缘的方法

    公开(公告)号：US20130008027A1

    公开(公告)日：2013-01-10

    申请号：US13635502

    申请日：2011-03-18

    申请人： Jean-Michel Patrick Maurice Franchet ,  Gilles Charles Casimir Klein

    发明人： Jean-Michel Patrick Maurice Franchet ,  Gilles Charles Casimir Klein

    IPC分类号： B23P15/04

    CPC分类号： B23P15/04 ,  B21D53/78 ,  B23K20/021 ,  B23K2101/001 ,  F01D5/147 ,  F01D5/282 ,  F04D29/324 ,  F05D2230/236 ,  F05D2230/50 ,  F05D2230/60 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49336 ,  Y10T29/49337

    摘要： A method for producing a metal insert for protecting a leading or trailing edge of a compressor vane of an aeronautical machine made of a composite material, by stamping sheets and diffusion bonding between the sheets. The method includes: initially shaping the sheets by stamping to approximate the sheets to a shape of a suction side and pressure side of the insert; producing a core shaped inner cavity of the metal insert to be manufactured, one of the surfaces thereof reproducing an inner shape of the suction side of the insert and the other surface reproducing an inner shape of the pressure side of the insert; positioning the sheets around the core and securing the assembly; applying a vacuum and sealing the assembly by bonding; assembling the assembly by hot isostatic compression; cutting the assembly to extract the core and separate the insert; producing an outer profile of the insert by a final machining.

    摘要翻译： 一种用于制造用于保护由复合材料制成的航空机械的压缩机叶片的前缘或后缘的金属插入件的方法，通过冲压片材和片材之间的扩散接合。 该方法包括：首先通过冲压来成形片材以将片材近似为插入物的吸力侧和压力侧的形状; 制造要制造的金属插入件的芯形内腔，其中一个表面再现插入件的吸入侧的内部形状，而另一个表面再现插入件的压力侧的内部形状; 将片材定位在芯部周围并固定组件; 施加真空并通过粘合密封组件; 通过热等静压进行装配; 切割组件以提取芯部并分离插入件; 通过最终加工产生插入件的外部轮廓。