压气机悬臂静叶流场非定常数值模拟

以现代高压压气机一排悬臂静叶与一排转叶组成的典型级为研究对象,采用非定常数值模拟方法,分析了非定常与定常数值模拟计算得出的级特性线以及峰值效率点气动参数在展向分布的差异,并对悬臂静叶内部流场结构进行了详细分析,结果表明:当悬臂静叶的轮毂设计间隙为2.5%叶高时,非定常计算的综合喘振裕度比定常大5.85%;在峰值效率点工况下,悬臂静叶总压损失和转子效率的非定常影响范围在10%以内,转叶进口相对气流角沿展向分布的影响在0.5°以内。悬臂静叶根部10%叶高以下区域出现了明显的泄漏流动,3.4%叶高压力系数变化最大,轮毂泄漏流起始于20%弦长附近,发展到70%弦长位置时泄漏损失最大,随后逐渐减弱.

Unsteady Numerical Simulation of Cantilevered Stator Flow Field

The typical stage of a modern high-pressure compressor with a row of cantilevered stator and a row of rotor is researched by using the unsteady numerical simulation method.This paper is focused on the difference of the overall performance of URANS and RANS numerical simulation,and the spanwise distribution of the aerodynamic parameters at the peak efficiency point.Through the analysis of the flow structure details of the cantilevered stator flow field,the results show that:When the design hub clearance of the cantilevered stator is 2.5% blade height,the stall margin of URANS is 5.85% higher than RANS.At the peak efficiency point,the variation of total pressure loss of cantilevered stator and efficiency of rotor caused by unsteady effect is less than 10%.The change of relative inlet flow angle of rotor is less than 0.50 due to unsteady effect.An obvious leakage flow starts from the 20% blade chord length mainly below the 10% blade height.The loss of the leakage flow reaches maximum at the 70% chord length and then gradually weakens.At the 3.4% blade height,the static pressure coefficient changes most.