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为了降低高负荷跨音速涡轮叶片流动损失,本文提出了一种在吸力面无遮盖段存在内凹型线的渐缩流道跨音速涡轮新叶型。新叶型可通过改进常规跨音速涡轮的叶型得到。数值模拟结果表明采用新叶型的平面叶栅与原叶型的相比总压损失系数降低了29.7%。通过分析新叶型的几何特征及其激波、膨胀波与压缩波的特点,揭示了新叶型使损失降低的内部流动机理。新叶型不仅能够减少气动损失,而且能够降低叶片排气的周向不均性,减小对下游叶片排边界层的非定常影响。
In order to reduce the flow loss of high-load transonic turbine blades, a new type of transonic turbine with a concave profile is proposed. The new leaf type can be obtained by improving the leaf shape of a conventional transonic turbine. The numerical simulation results show that the total pressure loss coefficient of the planar cascade with the new blade is reduced by 29.7% compared with that of the original blade. By analyzing the geometric characteristics of the new leaf and its characteristics of shock wave, expansion wave and compression wave, the internal flow mechanism of reducing the loss of the new leaf type is revealed. The new aerofoil can not only reduce the aerodynamic loss, but also reduce the circumferential unevenness of the vane exhaust and reduce the unsteady influence on the downstream vane boundary layer.