进气畸变对轴流压气机性能影响的准三维计算  

Quasi-3D calculation of influence of inlet distortion on axial flow compressor performance

作　　者：王永明[1] 胡骏[1] 邓艳[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2004年第4期343-348,共6页Journal of Propulsion Technology

摘　　要：为了提高分析进气畸变对轴流压气机气动性能和稳定性影响的能力,发展了一种沿叶高将压气机分割为若干个子压气机、采用二维可压缩非定常的Euler方程描述各子压气机回转面上无叶区的流动,并利用二维可压缩"激盘"取代各子压气机的转子和静子叶排的预测进气畸变影响的准三维模型。稳定边界的确定采用Koch的最大失速静压升系数法,并引用了临界畸变角的概念。计算分析了总温畸变、总压畸变以及总温 总压组合畸变沿多级轴流压气机的传递和对压气机性能和稳定性的影响。计算结果与现有的实验数据十分一致。To improve ability of analyzing the influence of inlet flow distortion on axial flow compressor performance, a quasi-three dimensional model was developed, which describes the flow fields in blade free sections using two dimensional, compressible and unsteady Euler equations for each sub-compressor, and replaces each blade row with a compressible actuator disk. The boundary stability was estimated by means of maximum pressure rise potential of axial compressor stages plus critical distortion angle. The transfer of total temperature distortion, total pressure distortion, combined total temperature-pressure distortion through compressors, as well as their influences on the compressor performance and stability were analyzed in detail. The computational results are consistent with the available experimental data.

关 键 词：轴流式压缩机 流场畸变 性能 稳定性 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]