基于通流程序的低速模拟气动设计及数值验证

Aerodynamic Design and Numerical Verification of Low-Speed Simulation Based on Throughflow Program

为了验证多级轴流压气机出口级性能,开展四级重复级低速模拟气动设计,并坚持以二维设计为主,三维数值验证为辅。利用相同的设计系统,建立了高低速压气机之间相似的二维流场和叶表无量速度分布。随后,低速与高速压气机三维数值计算结果对比表明,压升系数特性吻合,流场相似,且叶表无量纲速度由设计点到失速点保持一致的变化趋势,进一步验证了二维设计的可行性;利用相同的系统设计高、低速压气机,有利于形成高速-低速-高速的良性循环,有利于完善基于通流程序的设计体系,积累设计经验。

Low-speed simulation aerodynamic design with four repeating stages was conducted for verifying performance of a multistage axial compressor exit stage,and two-dimensional design was given first place with three-dimensional numerical verification as a supplement.Similar 2 D flowfield and profile surface normalized velocity distributions were established between low and high-speed compressor used the same design system.Then,the comparison between the 3 D numerical results of the low and high-speed compressors showed that the pressure rise coefficient characteristics were consistent,the flowfield was similar,and the dimensionless velocity of the blade surface kept the same trend from the design point to the stall point,which further validated the feasibility of2 D design.Using the same design system is conducive to forming a benign cycle of high-low-high speed,improving the design system based on througnflow program and accumulating design experience.