进气畸变对压气机性能影响的三维彻体力模型

基于三维彻体力模型理论初步发展了一个能有效预测进气畸变下压气机性能的压气机三维稳定性分析模型(CSAC).该模型通过求解带有源项的可压三维Euler方程组,对压气机内部全环三维流场进行模拟.叶片对气流的作用力和做功源项根据压气机三维稳态Navier-Stokes(N-S)解的相关气动参数计算得到,并给出了源项与叶片进口气动参数之间的数据库关联方法.利用该模型计算和分析了NASA Rotor 37在均匀进气下的气动性能,并与三维稳态N-S计算结果对比,验证了该模型的准确性.最后利用该模型模拟了Rotor 37在稳态周向总压畸变下的性能.结果表明:总压畸变不但降低了压气机的气动性能和稳定裕度,而且在压气机转子出口诱发总温畸变,研究表明该模型在消耗较少的计算资源下正确地反映了进气畸变对压气机性能的影响,是目前分析进气畸变对压气机性能影响的有力工具. 

Three-dimensional body-force model for effect on compressor performance of inlet distortion

A three-dimensional model called compressor stability analysis code (CSAC) was preliminarily developed to assess the effect of inlet distortion on aerodynamic performance of compressor.By solving the three-dimensional compressible Euler equations with the source item, the annular flow field of compressor interior could be simulated.The blade force and power source item were calculated with the aerodynamic parameters extracted from the three-dimensional steady-state Navier-Stokes (N-S) solutions.The way for correlating the source item with inlet aerodynamic parameters was also given. The aerodynamic performances of NASA Rotor 37 under clean inlet condition were calculated and analyzed with this model,the result under clean inlet was also compared with three-dimensional steady-state N-S solutions under the same inlet conditions. The accuracy of this model was verified.Finally,the performance of Rotor 37 under steady circumferential total pressure distortion was simulated.Results show that,total pressure distortion not only reduces the performance and the stability, but also induces total temperature distortion at the exit of compressor rotor.The research shows this model can correctly reflect the effect of distortion on compressor with much less compute resources, proving that this model is a suitable tool for compressor distortion analysis in current period.