摘要
超音叶型广泛应用于航空压气机,叶型的关键几何参数对其气动性能有重要影响。针对进气马赫数1.4的超音叶型,采用流场数值计算方法,研究叶型最大厚度、最大挠度及叶栅稠度对叶栅气动性能影响。研究表明:最大厚度及最大挠度变化对叶栅通道内激波结构影响很小;随着最大厚度的减小,最小损失对应的静压比增加并且耐反压能力增加,有利于实现更高压比设计;随着最大挠度减小,叶栅耐反压能力下降,最小损失近于不变,不利于高压比设计;增加稠度会造成槽道激波向叶栅通道上游偏移,直至形成脱体激波,使叶栅全工况损失增加。
Supersonic profiles are widely used in aviation compressors,and its key geometric parameters have an important impact on their aerodynamic performance.This paper aimed at inlet Mach number of 1.4,studies the influence of the maximum thickness,maximum deflection and cascade consistency on the aerodynamic performance of supersonic airfoil by the numerical calculation method of flow field.The results show that the variation of the maximum thickness and the maximum deflection has little effect on the shock structure in the cascade channel.With the decrease of the maximum thickness,the static pressure ratio corresponding to the minimum loss increases and the back pressure resistance increases,which is conducive to achieving higher pressure ratio design.And with the decrease of the maximum deflection,the back pressure resistance of the cascade decreases and the minimum loss remains almost unchanged,which is adverse to the design of the high pressure ratio.Increasing the consistency will cause the channel shock wave to shift to the upstream of the cascade channel until the detached shock wave is formed,which will increase the loss of the cascade under all operating conditions.
作者
韩壮壮
周正贵
HAN Zhuangzhuang;ZHOU Zhenggui(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《机械制造与自动化》
2024年第2期29-34,共6页
Machine Building & Automation
基金
国家科技重大专项项目(2017-II-0001-0013)。
关键词
超音叶型
关键几何参数
激波结构
流场性能
supersonic profile
key geometric parameters
shock wave structure
flow field performanc
