摘要
开展了旋转进气畸变对压气机气动稳定性影响的试验研究,试验结果表明旋转畸变网对压气机的气动稳定性和总静压升特性均有很大的影响.当畸变网与压气机相反旋转时,压气机的压升能力变化较小,稳定边界点流量系数变化不大;当两者转向相同时,进气畸变旋转频率对稳定边界点的压升系数和流量系数的影响均较大,尤其是在40%~60%转子转速范围内压气机的稳定性和压升能力急剧下降.通过对特征频率幅值变化的分析,认为畸变网转速在40%~60%转子转速范围内时,首先产生由畸变网后低压区诱导的旋转失速;随着压气机工作流量的继续降低,压气机进入其自然旋转失速状态.失速起始过程的试验结果表明,旋转进气畸变对于该压气机的失速起始特性未产生影响,表现为模态波失速起始的特征.
Effects of rotating inlet distortion on the aerodynamic stability of compressor were carried out in a 2-stage low speed compressor. The results show that the rotating screen in the upstream has great impact on the aerodynamic stability and total static pressure rise ratio of the compressor. When the rotating screen rotates at a different direction with the compressor, the pressure rise ratio and flow coefficient of stable boundary point vary lit tle. If both have the same rotation direction, the speed of the rotating screen has big effect on both of the stability and the pressure rise ratio, especially between 40-60 percent of rotor speed. Through analysis of the variation of amplitude of characteristic frequency, it＇s concluded that the rotating stall induced by the low-total-pressure area produced by rotating screen will appear in the compressor. If the mass flow continues to decrease, the compressor will enter into natural rotating stall state. The experimental results of stall inception process reveal that the rotating inlet distortion can＇t affect the stall inception of the compressor.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第11期2095-2100,共6页
Journal of Aerospace Power
基金
国家973项目(20007CB210301)
关键词
压气机
旋转进气畸变
稳定性
试验
compressor
rotating inlet distortion
stability
experiment
