对转压气机转速比变化对稳定边界的影响  

Effects of Rotational Speed Ratio on Stability Boundary of Contra-Rotating Compressor

作　　者：高丽敏[1] 李晓军[1] 冯旭栋[1] 谢建[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2012年第6期881-887,共7页Journal of Propulsion Technology

摘　　要：以实验室对转压气机为研究对象,采用数值模拟方法研究了不同转速比对压气机稳定性的影响。着重分析了转速比对压气机失速边界和堵塞边界的影响规律,并对不同转速比下各转子的稳定性进行了初步的研究。结果表明:(1)当转速比R2:R1>1.0时,转速比增大会导致失速边界和堵塞边界均向小流量方向偏移。(2)当转速比R2:R1<1.0时,随转速比增大失速边界变化不大,但堵塞边界向大流量方向偏移。(3)转子1转速变化对转子2气动性能具有很大的影响,而转子2转速变化却对转子1性能影响不大。(4)在不同转速比下,导致该对转压气机失稳的主要因素也不同。The effects of rotational speed ratio on stability of two-stage contra-rotating compressors with the numeral meth- od were studied. The effect law of rotational speed ratio on stall boundary and block boundary was analyzed. The stability of rotors in different rotational speed ratio was studied. The results show that ： （ 1 ） when the rotational speed ratio R2 ：R1 〉 1.0, the stall boundary and block boundary will deflect to low flow direction with increasing the rotational speed ratio. （2） When the rotational speed ratio R2：R1 〈 1.0, the stall boundary will not change, but the block boundary will deflect to low flow di- rection with increasing the rotational speed ratio. （3） The variation of rotational speed of the first rotor has strong effect on the performance of the second rotor. But the speed variation of the second rotor has little effect on the performance of the first ro- tor. （4）The factors resulting in destabilization of contra-rotating compressor will differ with different rotational speed ratio.

关 键 词：对转压气机 数值模拟 转速比 稳定边界 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]