Compressor Rotor for Gas Turbine Engine With Deep Blade Groove
    2.
    发明申请
    Compressor Rotor for Gas Turbine Engine With Deep Blade Groove 审中-公开
    具有深叶片槽的燃气轮机发动机的压缩机转子

    公开(公告)号:US20140182293A1

    公开(公告)日:2014-07-03

    申请号:US13731147

    申请日:2012-12-31

    Abstract: A compressor rotor has a rotor centered on an axis, and a groove with opposed side edges. The groove receives a plurality of removable compressor blades, and has tangential sides. The tangential side surfaces are in contact with said tangential sides of the groove, and at least one slot is cut into the side edges. A first radial distance is measured from a radially outer edge of the side edge to a radially outer beginning point of the tangential sides of the groove. A second radial distance is radially between the radially outer beginning point of the tangential sides to a radially inner end of the tangential sides of the groove. A ratio of the first and second radial distance is between 1.1 and 5.0.

    Abstract translation: 压缩机转子具有以轴为中心的转子和具有相对侧边缘的槽。 凹槽接收多个可移除的压缩机叶片,并具有切向侧。 切向侧表面与凹槽的所述切向侧面接触,并且至少一个狭槽被切入侧边缘。 第一径向距离是从侧边缘的径向外边缘到凹槽的切向边的径向外开始点测量的。 第二径向距离在切线侧的径向外部起始点与槽的切向侧的径向内端之间径向地形成。 第一和第二径向距离的比率在1.1和5.0之间。

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