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Turbine engine blade attachment element with first dovetail slot whose length is greater than that of a second dovetail slot.

机译:涡轮发动机叶片附接元件具有第一燕尾槽,该燕尾槽的长度大于第二燕尾槽的长度。

摘要

A turbine engine (100) has a rotating member (130), which in turn has an axial centerline and a blade fixing member. The blade attachment member defines a first dovetail slot (232) defining a first axial length parallel to the axial centerline. The blade mounting member also defines a second dovetail slot (234) defining a second axial length parallel to the axial centerline. The first axial length is greater than the second axial length, and at least a portion of the second dovetail slot extends over at least a portion of the first dovetail slot.
机译:涡轮发动机(100)具有旋转构件(130),该旋转构件又具有轴向中心线和叶片固定构件。刀片附接构件限定第一燕尾槽(232),第一燕尾槽(232)限定平行于轴向中心线的第一轴向长度。刀片安装构件还限定第二燕尾槽(234),第二燕尾槽(234)限定平行于轴向中心线的第二轴向长度。第一轴向长度大于第二轴向长度,并且第二燕尾槽的至少一部分在第一燕尾槽的至少一部分上延伸。

著录项

  • 公开/公告号CH701310B1

    专利类型

  • 公开/公告日2015-02-13

    原文格式PDF

  • 申请/专利权人 GENERAL ELECTRIC COMPANY;

    申请/专利号CH20100001029

  • 发明设计人 DONALD JOSEPH KASPERSKI;

    申请日2010-06-24

  • 分类号F01D5/30;

  • 国家 CH

  • 入库时间 2022-08-21 14:56:04

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