中文摘要：

本文采用数值模拟的方法对具有缩放型流道动叶的涡轮级中的激波结构进行了数值研究。在近设计工况下，随叶高的不同，缩放型流道动叶尾缘的相对马赫数分布不同，尾缘燕尾型激波的强弱及其在相邻叶片吸力面的反射波也不同。由于叶片吸力面60％轴向弦长处为一内凹壁面，在该处将会产生一束较强的微弱压缩波，在叶片顶部，该微弱压缩波在通过燕尾波后不远处即发展为一较强的斜激波。随背压增加，动叶尾缘燕尾形激波及其在相邻叶片吸力面上反射波的强度会发生变化，一般来说会减弱，但叶顶由于微弱压缩波所形成的激波会得到强化。

英文摘要：

Detailed numerical simulations have been carried out to investigate the shock systems in a converging-diverging nozzle rotor turbine stage. Near the design point, along the rotor span, the contours of the relative Mach number near the rotor trailing edge are different, and the strength of the fishtail shock and its echo wave on the suction surface of the adjacent rotor is also different. A group of weak pressure wave produces from the suction surface after about 60% axial chord of the rotor, where there has a concave wall. On the 87.5% span of the rotor, the weak pressure wave will develop to an oblique shock. The strength both of the fishtail shock and its echo wave varies with the increasing of the outlet static pressure of the turbine stage, generally which weakens, but on the 87.5% span of the rotor, the oblique shock developed by the weak pressure wave is intensified.