叶尖间隙对跨声速轴流压气机近失速的影响

以跨声速轴流压气机rotor 37为研究对象,利用数值仿真计算方法,采用高密度网格对跨声速轴流压气机设计间隙、1/2设计间隙、1/4设计间隙、2倍设计间隙以及零间隙下近失速状况进行计算.计算结果显示:由设计间隙减小到1/2设计间隙时,跨声速轴流压气机压升和绝热效率损失不大,跨声速轴流压气机失速裕度却提高了4%.在此基础上,引入失速分类方法以及涡动力学理论,对流场进行细节分析.提出适当改变间隙可以有效地拓宽跨声速轴流压气机稳定工作范围,但是间隙改变对泄漏涡破碎以及边界层分离有着重要的影响,甚至诱导不同的失速形式,为跨声速轴流压气机间隙设计提供参考,并且从气动角度探讨在跨声速轴流压气机中应用间隙控制技术的条件.

Influence of blade tip clearance at near-stall condition on transonic axial-flow compressor

Numerical simulation with high density grid was carried out to study blade tip clearance of a transonic axial-flow compressor rotor 37 at near-stall condition. The blade tip clearance included design clearance, half design clearance, quarter design clearance,2 times design clearance and zero clearance. The results show that stall margin is improved 4%, and adiabatic efficiency and pressure ratio don't decline obviously, when the blade tip clearance reduced from design clearance to half design clearance. Details of the flow field were analyzed based on different stall forms and vortex dynamics. The change of clearance may improve stability margin greatly and clearance plays an important role in leakage vortex and separation of boundary layer, or even induces different stall forms. This has provided necessary basic research for design of the compressor are provided, and discussed the application condition of clearance control technology in aerodynamics.