叶片稠度对压气机最大有效静压升影响的数值模拟  

Numerical Simulation of Influence of Blade Number on Maximum Effective Static Pressure Rise of Compressor

作　　者：王同辉[1] 王志强[1] 王学高 WANG Tonghui;WANG Zhiqiang;WANG Xuegao(College of Energy and Power Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2022年第4期662-669,共8页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：为研究叶片稠度对压气机最大有效静压升的影响,针对某单级低速压气机,通过改变转静子叶片数,构建了不同叶片稠度的压气机模型,采用三维数值模拟的方法,获得了不同稠度情况下的压气机特性。计算结果表明,静子叶片数的增加能够抑制附面层分离,拓宽压气机稳定工作范围,压气机近失速点的压比增大,压气机的最大压升能力增强,其最大有效静压升增大;转子叶片数的增加能够抑制气流分离,减小流动损失,从而使得近失速工况下压气机效率和压比增大,压气机近失速点压升能力增强,其最大有效静压升增大。通过对叶片数不同时各压气机的最大有效静压升系数与Koch最大有效静压升预测曲线的对比,从数值模拟的角度验证了以最大有效静压升作为压气机稳定性判据的有效性。In order to study the effect of blade consistency on the maximum effective static pressure rise of a single-stage low-speed compressor,a compressor model with different blade consistency is constructed by changing the number of rotor stator blades.The compressor characteristics under different consistency are obtained by using three-dimensional numerical simulation method.The results show that the increase of stator blade number can inhibit the boundary layer separation,delay the compressor to enter the numerical stall,increase the pressure ratio near the stall point,enhance the maximum pressure rise capacity of the compressor,and increase the maximum effective static pressure rise;the increase of the number of rotor blades can inhibit the flow separation and reduce the flow loss,so as to reduce the pressure drop in the low flow condition with the increase of compressor efficiency and pressure ratio,the ability of pressure rise near stall point increases,and the maximum effective static pressure rise increases.By comparing the maximum static pressure rise coefficient of each compressor with Koch correlation curve when the number of blades is different,the effectiveness of using the maximum static pressure rise as the compressor stability criterion is verified from the perspective of numerical simulation.

关 键 词：压气机 叶片数 最大有效静压升 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]