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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.
A three-dimensional stability analysis model (CSAC) of a compressor that can effectively predict the compressor performance under intake distortions is initially developed based on the three-dimensional Thorough-body Model theory. By solving the compressible three-dimensional Euler equations with source terms, The whole three-dimensional flow field inside the machine was simulated.The force acting on the airflow and the power source were calculated according to the related aerodynamic parameters of the three-dimensional Navier-Stokes (NS) solution of the compressor, Parameters of the database association between the use of the model to calculate and analyze the NASA Rotor 37 at uniform inlet aerodynamic performance, and compared with three-dimensional steady-state NS calculated results verify the accuracy of the model.Finally, the use of the model to simulate The results show that the total pressure distortion not only reduces the aerodynamic performance and the stability margin of the compressor, but also induces the total temperature distortion at the exit of the compressor rotor. The results show that the model is stable under the steady state total circumferential pressure distortion The computational resources with less consumption correctly reflect the influence of intake distortion on the performance of the compressor, which is a powerful tool to analyze the influence of intake distortion on the performance of the compressor.