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    Turbine blade with enhanced cooling and profile optimization
    1.
    发明授权
    Turbine blade with enhanced cooling and profile optimization 失效
    涡轮叶片具有增强的冷却和轮廓优化

    公开(公告)号：US5980209A

    公开(公告)日：1999-11-09

    申请号：US884091

    申请日：1997-06-27

    申请人： Vincent Anthony Barry ,  Brent A. Gregory ,  Nesim Abuaf

    发明人： Vincent Anthony Barry ,  Brent A. Gregory ,  Nesim Abuaf

    IPC分类号： F01D5/14 ,  F01D5/18 ,  F01D5/30

    CPC分类号： F01D5/141 ,  F01D5/187 ,  Y10S416/05

    摘要： A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil.

    摘要翻译： 第一级涡轮机叶片包括具有根据表I的轮廓的翼型件。翼型件具有多个冷却空气通道，该冷却空气通道从翼部的根部直线延伸到翼型部分。 叶片包括具有一对空腔的柄，所述一对空腔通过叶片燕尾榫与在车轮空间中的增压室连通，用于向翼型中的通道供应冷却空气。 翼型件中的冷却通道终止在尖端部分处的凹部中，该凹部具有与翼型件的后缘相邻并且沿着吸力侧的开口，以使冷却空气能够排出到翼型的低压侧上的热气流中。 大部分冷却通道是混浊的。 这些通道中的某些通道排列成与翼型的压力和吸力侧相邻的排。