1.5级跨音速压气机内部流场数值分析

NUMERICAL INVESTIGATION OF FLOW FIELD IN A 1.5-STAGE TRANSONIC COMPRESSOR

本文以正在建设的1.5级跨音压气机试验台所采用的压气机为研究对象,利用NUMECA软件计算了该压气机在不同转速下的特性曲线,并在设计转速下,对其内部流场进行了分析研究。研究表明:激波位置和强度随压气机运行工况的变化而变化;在近失速工况和堵塞工况时,压气机内部流动出现分离;在设计工况时,压气机内部流动状况良好。上述结论,可以为试验台建设中,探头位置的确定和激光测窗位置的选取等提供指导和帮助。此外,该算例作为一盲解,将来同实验结果对比后,可以用来检验和校准CFD程序,为国内F级燃机设计平台的建设打下良好的基础。

A 1.5-stage compressor, used in a 1.5-stage transonic compressor test rig, is investigated by the NUMECA software in the paper and the performance curves at six different rotational speeds are calculated. Then the flow field in the compressor at the design rotational speed is analyzed. The results show that the location and the intensity of the shock vary with the operating condition. And the separation occurs in the near stall condition and the choke condition and the flow condition are quite well in the design condition. The results can help and guide the choice of the probe locations and the laser measure window locations when the test rig is built. Besides, as a blind case, it can be used to test and calibrate the CFD code after the results will be compared with the experimental results. Thus, it can supply some useful information for the study of an F-class gas turbine.