本文针对全转速汽轮机1500mm末级动叶片顶部专用超音速叶型的激波结构和变工况气动性能开展研究。采用数值模拟方法分析了进口马赫数从0.9到1.3、出口等熵马赫数从1.42到2.48范围内的流动情况。结果表明，激波结构主要由前缘波及其两次反射波、尾缘波及其一次反射波组成。叶型损失随出口等熵马赫数增加而下降，进口马赫数为0.9和1.3时，出口等熵马赫数从1.42增加到2.48的能量损失系数分别降低0.016（42%）和0.097（66%）；叶型损失随进口马赫数减小而降低，出口等熵马赫数为1.42时，进口马赫数从1.3降到0.9的能量损失系数降低0.1（74%），而在出口等熵马赫数为2.48时，仅降低0.028（58%）。造成这种变化的原因与尾迹区和激波强度的变化密切相关。

This paper conducts research on the shock wave structure and off-design performance of the special supersonic blade profile at the top of the 1500 mm moving blade for ultra-long last-stage of full-speed steam turbine. By using the numerical simulation method, the flow conditions within the range of inlet Mach number from 0.9 to 1.3 and outlet isentropic Mach number from 1.42 to 2.48 are analyzed. The results show that the shock wave structure of the blade profile is mainly composed of the leading-edge wave and its two reflected waves, as well as the trailing-edge wave and its one reflected wave. The blade profile loss decreases with the increase of the outlet isentropic Mach number. When the inlet Mach numbers are 0.9 and 1.3 respectively, as the outlet isentropic Mach number increases from 1.42 to 2.48, the energy loss coefficients decrease by0.016 (42%) and 0.097 (66%) respectively; the blade profile loss increases with the decrease of the inlet Mach number. When the outlet isentropic Mach number is 1.42, the energy loss coefficient of the inlet Mach number 1.3 is 0.1 (74%) lower than that of 0.9, while when the outlet isentropic Mach number is 2.48, it only decreases by 0.028(58%). The reasons for these changes are closely related to the changes in the wake region and the intensity of the shock waves.