畸变进气下压气机三维黏性数值计算模型  

Investigation of three-dimensional viscous model for compressor with distortion inlet

作　　者：时培杰[1] 乔渭阳[1] 魏佐君[1] 陈萍萍[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2012年第7期1472-1478,共7页Journal of Aerospace Power

摘　　要：通过对压气机环形无叶片通道求解带源项的N-S(Navier-Stokes)方程,实现对压气机全通道流场的计算,建立了压气机三维黏性非定常数值计算模型.源项是由三维计算流体动力学(CFD)求解器定常计算的气流参数计算得到,求得不同工作点源项大小,然后根据进口参数对源项插值得到当前计算点源项.采用该模型对某跨声速单级压气机在均匀进气下性能和流场的计算结果与实验结果进行了对比,两者能够较好的一致,验证了模型的可靠性;之后应用该模型对周向总压畸变进气下的流场和性能进行了计算,分析了畸变进气对压气机三维流场和性能的影响,并引入压气机失稳判据分析畸变对压气机稳定性的影响.A three-dimensional model for predicting compressor performance and stabili- ty was developed by solving N-S （Navier-Stokes） equation with source terms to annulus duct without blades. The source terms were calculated by flow field parameters which were generated by conventional three-dimensional computational fluid dynamics （CFD） solver at different operation conditions. A transionic single-stage compressor was investigated by the model with clean inlet. The three-dimensional flow field and performance of CFD results a- greed well with those of the experiment, which indicat that the model is reliable and correct. Finally, the effect of circumferential total-pressure distortion on the compresser flow and performance was studied with the model. The compressor stability was further analyzed by introducing the stall criterion.

关 键 词：计算模型 黏性 求解器 源项 畸变进气 性能 稳定性 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]