HYBRID AIRFOIL FOR A GAS TURBINE ENGINE
    11.
    发明申请
    HYBRID AIRFOIL FOR A GAS TURBINE ENGINE 审中-公开
    燃气涡轮发动机的混合式机翼

    公开(公告)号:WO2014011242A2

    公开(公告)日:2014-01-16

    申请号:PCT/US2013/032918

    申请日:2013-03-19

    Abstract: A hybrid airfoil for a gas turbine engine according to an exemplary embodiment of this disclosure can include a leading edge portion, a trailing edge portion, and an intermediate portion between the leading edge portion and the trailing edge portion. The leading edge portion can be made of a first material, the trailing edge portion can be made of a second material, and the intermediate portion can be made of a third material. At least two of the first material, the second material and the third material are different materials.

    Abstract translation: 根据本公开的示例性实施例的用于燃气涡轮发动机的混合翼型可以包括前缘部分,后缘部分以及在前缘部分和后缘部分之间的中间部分 。 前缘部分可以由第一材料制成,后缘部分可以由第二材料制成,并且中间部分可以由第三材料制成。 第一种材料,第二种材料和第三种材料中的至少两种是不同的材料。

    LEADING EDGE PROTECTION AND METHOD OF MAKING
    12.
    发明申请
    LEADING EDGE PROTECTION AND METHOD OF MAKING 审中-公开
    领先的边缘保护和制作方法

    公开(公告)号:WO2013172894A2

    公开(公告)日:2013-11-21

    申请号:PCT/US2013/026663

    申请日:2013-02-19

    Abstract: A method of forming a leading edge protection component includes depositing particles using a cold spray process on a mandrel to form a leading edge protection component; and removing the leading edge protection structure from the mandrel. The leading edge protection can be formed in one or more pieces and involve using one or more mandrels.

    Abstract translation: 形成前缘保护部件的方法包括使用冷喷涂工艺在芯棒上沉积颗粒以形成前缘保护部件; 并从心轴移除前缘保护结构。 前缘保护可以形成在一个或多个部件中并涉及使用一个或多个心轴。

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