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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.
Taking transonic axial flow compressor rotor 37 as the research object, the numerical simulation calculation method was used to design the cross-axial axial compressor design clearance, 1/2 design clearance, 1/4 design clearance and 2 times design clearance And the near-zero stall condition under zero clearance is calculated.The results show that when the design clearance is reduced to 1/2 design clearance, the pressure loss and adiabatic efficiency of the transonic axial-flow compressor are not large, But the degree is increased by 4% .Based on this, the method of straggling classification and the theory of eddy dynamics are introduced to make detailed analysis of the flow field.It is proposed that the appropriate change of clearance can effectively expand the stable working range of transonic axial-flow compressor, It has an important influence on the crushing of the leakage vortex and the separation of the boundary layer, and even induces different stall modes, which provides a reference for the design of transonic axial-flow compressor clearance. The aerodynamic application of the gap control technology in transonic axial-flow compressors condition.