摘要
针对多级轴流压气机进行进气深度节流试验,通过对试验器进口节流阀的调节,对比了不同进口节流比条件下试验件的特性,开展了低雷诺数效应对其性能的影响分析,并利用数值计算方法研究了进口低雷诺数效应对试验件特性的影响机理。结果表明:随着压气机进口节流比的降低,进口雷诺数逐渐降低,试验件性能也逐渐降低,具体表现为压气机流量、压比、效率的降低;当压气机进口雷诺数降低到一定程度后,各级转子激波明显外推,叶片附面层明显增厚,造成各级做功能力下降,试验件内部流场展向的不均匀性也逐渐增大,最终导致压气机性能衰减。
For deep throttling test of a multi-stage axial flow compressor,by adjusting the inlet throttle valve of the tester,the characteristics of the test pieces under different inlet throttling ratios were compared,and the influence of low Reynolds number effect on their performance was analyzed.The influence mechanism of low Reynolds number effect on the characteristics of the test piece was studied by numerical calculation.The results show that:1)With the decrease of compressors inlet throttling ratio,the inlet Reynolds number gradually decreases,and the performance of test parts also gradually decreases,which is manifested in the decrease of compress flow,pressure ratio and efficiency.2)When the Reynolds number at the inlet of the compressor is reduced to a certain extent,the shock wave at each stage of the rotor is obviously extrapolated,and the blade boundary layer is obviously thickened,resulting in the reduction of the word capacity at each stage,the spread inhomogeneity of the flow field in the compressor also increases gradually,and finally leading to the performance degradation of the compressor.
作者
赵正
吴森林
张毅
刘宽
张晓良
刘晓晨
ZHAO Zheng;WU Senlin;ZHANG Yi;LIU Kuan;ZHANG Xiaoliang;LIU Xiaochen(AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China)
出处
《燃气涡轮试验与研究》
2023年第6期8-12,共5页
Gas Turbine Experiment and Research
关键词
航空发动机
雷诺数效应
压气机
节流比
气动性能
附面层
机理分析
aero-engine
Reynolds number effect
compressor
throttling ratio
aerodynamic performance
boundary layer
mechanism analysis
