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    • 9. 发明授权
    • Gas-turbine blade and method of manufacturing a gas-turbine blade
    • 燃气轮机叶片及其制造方法
    • US06582194B1
    • 2003-06-24
    • US09515177
    • 2000-02-29
    • Jens BirknerKnut Halberstadt
    • Jens BirknerKnut Halberstadt
    • F03D1102
    • B23P15/04F01D5/187F05D2230/10F05D2230/22F05D2260/2212
    • The invention relates to a method of manufacturing a gas-trubine blade and to a turbine blade. First, a hollow, supporting metal blade body is made, in particular by casting, with a multiplicity of, in particular peg-like, elevations on an outer surface of a blade airfoil of the metal blade body. Impact cooling bores are bored between the elevations from the outer surface to the hollow interior space of the metal blade body. A coating is applied which fills the intermediate spaces between the elevations and closes the impact cooling bores. The coating is made of a heat-resistant, removable material. Then, a covering coat is adhered to the metallically bright top sides of the elevations, and the material in the intermediate spaces between the elevations of the metal blade body and the covering coat is then removed.
    • 本发明涉及一种制造气体涡流叶片和涡轮叶片的方法。 首先,通过在金属刀片体的叶片翼型的外表面上形成多个特别是钉状的凸起,特别是通过铸造制成中空的支撑金属刀片体。 冲击冷却孔在从金属刀片体的外表面到中空的内部空间的高度之间钻孔。 施加涂层,其填充高度之间的中间空间并且关闭冲击冷却孔。 涂层由耐热,可拆卸的材料制成。 然后,将覆盖层粘附到高度的金属光亮的顶侧,然后去除金属刀片体的高度和覆盖层之间的中间空间中的材料。