基于转静干涉效应的压气机叶片气动载荷分析

Aerodynamic load analysis of compressor blade based on stator-rotor interaction effect

转静叶排的相互作用会使压气机内部流场存在复杂的非定常性。为深入研究压气机叶片的气动载荷特性,以某型航空发动机压气机为研究对象,考虑叶排间的转静干涉效应,利用滑移网格技术对整个叶盘的三维流场展开模拟,求解干涉周期Tb内压气机转子内部的流动规律。同时对叶片气动载荷的非定常特性进行进一步分析,讨论了不同压比、转速对压气机叶片气动载荷的影响。结果表明叶片压力面和吸力面气动载荷波动峰值的主导频率皆为转静干涉频率f0的倍频,其中一倍频(1×f0)分量占主导地位。在干涉周期Tb内,叶片表面压力涡发生周期性的迁移与耗散,压力面和吸力面气动载荷的变化呈相反趋势。随着压比的增加,压气机叶片气动载荷逐渐增大,但其脉动幅值和频谱峰值基本不变。转速的升高使得转静干涉的频率增大,增强了压气机叶片气动载荷的非定常特性。研究结果能够应用于叶盘结构的气动优化设计,可为高性能航空发动机压气机的研制提供支持和参考。

Due to the interaction of stator-rotor blade rows, the compressor internal flow field is unsteady and complex. In order to further research on the characteristics of compressor blade aerodynamic load, an aero-engine compressor is selected as the research object. Based on the stator-rotor interaction effect between blade rows, the three-dimensional flow field of the whole blade-disk was simulated by sliding mesh. Then, the internal flow law of compressor rotor in the interference period Tb was solved and the unsteady aerodynamic load on the compressor blade was analyzed, and the effect of different pressure ratios and rotational speeds on the blade aerodynamic load was discussed. The results showed that dominant pulsation frequencies of the peak value of aerodynamic load on blade pressure and suction surfaces were mainly at frequency doubling of stator-rotor interaction, especially at one time frequency （1×f0）. Within the interaction period Tb, pressure vortexes of blade surface transmitted and dissipated periodically, and the variation of aerodynamic load on pressure and suction surfaces took the opposite trend. The magnitude of aerodynamic load increased with the pressure ratio, but the pulsation amplitude and the peak value were basically unchanged. The increase of rotational speed made the frequency of stator-rotor interaction much higher, and enhanced the unsteady characteristic of aerodynamic load. The results can be applied to aerodynamic optimization design of the blade-disk structure, which can provide support and reference for the development of high performance aero-engine compressor.