改进的离心压气机滑移因子模型  

Improved slip factor model for centrifugal compressor

作　　者：张超炜 董学智[1,2] 刘锡阳 高庆[1,2] 谭春青 ZHANG Chaowei;DONG Xuezhi;LIU Xiyang;GAO Qing;TAN Chunqing(Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院大学工程科学学院,北京100049

出　　处：《航空动力学报》2018年第9期2178-2187,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(51676182)

摘　　要：建立一种基于Qiu模型的改进的离心压气机滑移因子模型。该模型在Qiu模型的基础上,增添二次流项来修正滑移因子,同时考虑了出口叶片角与最大叶片角的差值及相应位置。采用亚声速叶轮Krain4、跨声速叶轮Krain6和IET200叶轮对该改进模型进行CFD验证,并对模型二次流项中常系数c的取值进行讨论。结果表明:与Qiu模型及其他传统滑移因子模型相比,该改进模型的精度较高,平均相对误差在2%以下,适用于亚声速及跨声速离心压气机。An improved slip factor model based on Qiu model for centrifugal compressor was developed.A secondary flow term was added to the Qiu model to correct the slip factor.Furthermore,the difference between the exit blade angle and the maximum blade angle as well as the corresponding position was taken into account.The improved model was verified by CFD with subsonic impeller Krain4,transonic impeller Krain6 and IET200 impeller.The constant coefficient c of the secondary flow was discussed.Compared with the CFD results,there as small error of the improved model.Results showed that compared with Qiu model and other traditional slip factor model,the improved model had higher accuracy,and the average relative error was below 2%.This improved model is suitable for subsonic and transonic centrifugal compressors.

关 键 词：滑移因子 离心压气机 相对涡 Qiu模型 二次流 扩压因子 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]