Method and apparatus for closing holes in superalloy gas turbine blades
    1.
    发明授权
    Method and apparatus for closing holes in superalloy gas turbine blades 有权
    用于关闭超合金燃气轮机叶片中的孔的方法和装置

    公开(公告)号:US06413041B1

    公开(公告)日:2002-07-02

    申请号:US09631095

    申请日:2000-08-02

    IPC分类号: F03B1100

    摘要: A sealing member that seals a core printout hole in a turbine blade of a combustion gas turbine engine includes a plug member and first and second leg members. The plug member is formed generally in a top hat configuration and is disposed in a cavity formed in the blade, the plug member being retained in the desired sealing position by the leg members. The plug member broadly serves the purpose of sealing the hole that is in communication with the cavity. The plug member includes a substantially planar plate that is disposed adjacent the internal first surface of a wall of the turbine blade and a retention member that is received in the hole. The first and second leg members are fixedly mounted, such as by welding, on the plug member and are at least partially disposed adjacent and overlap a second opposite and external surface of the wall.

    摘要翻译: 密封燃烧燃气涡轮发动机的涡轮叶片中的核心打印孔的密封构件包括塞构件和第一和第二腿构件。 插头构件大致形成为顶帽构造,并且设置在形成在叶片中的空腔中,插头构件由腿构件保持在期望的密封位置。 插塞构件广泛地用于密封与空腔连通的孔。 插塞构件包括基本上平面的板,其邻近于涡轮叶片的壁的内部第一表面设置,并且保持构件被容纳在孔中。 第一和第二腿构件例如通过焊接固定地安装在塞子构件上并且至少部分地布置成与壁的第二相对和外表面相邻并重叠。