摘要
本文针对 RB-1 99五级高压压气机 ,实验研究了进口周向总压畸变和旋流畸变对其性能和失速边界的影响 ,获得了进口总压畸变度和周向畸变角变化 ,以及进气气流方向角不均匀时 ,RB-1 99五级高压压气机性能变化的详细实验数据 。
The inlet flow distortion effects in a five stage compressor have been investigated experimentally.The inlet total pressure distortion and swirl distortion have been generated by inserting perforated screens and guide vanes respectively into the compressor inlet duct.It has been found that both inlet total pressure distortion and swirl distortion have strong effects on the performance and stability of the compressor.With the increase in the angular width of the low inlet total pressure,both the pressure ratio and efficiency of the compressor decrease, and the loss of surge pressure ratio of the compressor increases when the distorted sector angle less than 60°.The inlet swirl distortion has a stronger effect on the loss of surge pressure ratio than the influence of inlet total pressure distortion.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2001年第2期142-146,共5页
Journal of Aerospace Power
