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    AIRFOIL HAVING AN EROSION-RESISTANT COATING THEREON
    1.
    发明申请
    AIRFOIL HAVING AN EROSION-RESISTANT COATING THEREON 审中-公开
    具有抗腐蚀涂层的空气

    公开(公告)号：US20140301861A1

    公开(公告)日：2014-10-09

    申请号：US14172435

    申请日：2014-02-04

    Applicant: General Electric Company

    Inventor： Robert William Bruce ,  Aaron Dennis Gastrich ,  John William Hanify ,  Roger Owen Barbe

    IPC: F01D5/28 ,  C23C16/44

    CPC classification number: F01D5/28 ,  C23C16/44 ,  F01D5/288 ,  F04D29/023 ,  F04D29/324 ,  F05D2230/313 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2300/228 ,  F05D2300/611 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A compressor blade having an airfoil that comprises oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, a forward-most nose of the airfoil located at the leading edge and having a profile, a blade tip, and an erosion-resistant coating. The coating is present on the concave surface near the trailing edge, optionally present on the nose, optionally present on the convex surface, wherein the convex surface is free of the erosion resistant coating within at least 20% of the chord length from the nose. The thickness of the coating on the concave surface, the convex surface, and the nose is such that, if the gas turbine engine is exposed to an erosive environment, deterioration of the concave surface, the convex surface and the leading edge does not form a pronounced cusp at an intersection of the convex surface and leading edge.

    Abstract translation: 一种压缩机叶片，其具有包括相对设置的凸形和凹形表面的翼型，相对设置的前缘和后缘在其间限定翼型的弦长，位于前缘并具有轮廓的翼型的最前端， 叶片尖端和耐侵蚀涂层。 涂层存在于靠近后缘的凹面上，任选地存在于鼻部上，任选存在于凸表面上，其中凸起表面在距离鼻子的弦长的至少20％内没有抗侵蚀涂层。 凹面，凸面，鼻部的涂层厚度使得如果燃气涡轮发动机暴露于侵蚀环境，则凹面，凸面和前缘的劣化不会形成 在凸面和前缘的交点处发音尖。

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