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本文研究分析了三套涡轮平面叶栅设计攻角下变出口等熵马赫数时的气动性能,给出了三套涡轮叶栅设计攻角下的临界马赫数;阐述了叶栅出口总压恢复系数、能量损失系数、负荷系数及进口马赫数随出口等熵马赫数的变化规律;分析了叶片表面和叶栅端壁静压系数及等熵马赫数的分布情况。结果表明,三套叶栅所采用的叶型具有后部加载特性,具有较好的气动性能;叶栅出口能量损失系数随出口等熵马赫数的变化呈现出先减小后增大的变化规律。
In this paper, the aerodynamic performance of three turbo-cascade cascades at different angles of attack is analyzed, and the critical Mach number of the three cascades is given. The total pressure recovery Coefficient, coefficient of energy loss, load coefficient and Mach number of inlet with the change of isentropic Mach number of outlet. The distribution of static pressure coefficient and isentropic Mach number of blade surface and cascade endwall were analyzed. The results show that the three types of cascades have posterior loading characteristics and good aerodynamic performance. The energy loss coefficient at exit of cascades decreases first and then increases with the change of outlet isentropic Mach number.