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张超炜,董学智,刘锡阳,高庆,谭春青.离心压气机叶顶泄漏涡轨迹数值模拟及失速预测[J].航空动力学报,2019,34(7):1586~1597
离心压气机叶顶泄漏涡轨迹数值模拟及失速预测
Numerical simulation of tip leakage vortex trajectory and stall prediction for centrifugal impeller
投稿时间:2019-01-04  
DOI:10.13224/j.cnki.jasp.2019.07.020
中文关键词:  离心压气机  叶顶间隙  叶顶泄漏涡轨迹  主流/叶顶泄漏流交界面  失速预测
英文关键词:centrifugal impeller  tip clearance  tip leakage vortex trajectory  interface between main flow and tip leakage flow  stall prediction
基金项目:国家重点研发计划(2018YFB0905101)
作者单位
张超炜 中国科学院 工程热物理研究所,北京 100190
中国科学院大学 工程科学学院,北京 100049 
董学智 中国科学院 工程热物理研究所,北京 100190
中国科学院大学 工程科学学院,北京 100049 
刘锡阳 中国科学院 工程热物理研究所,北京 100190
中国科学院大学 工程科学学院,北京 100049 
高庆 中国科学院 工程热物理研究所,北京 100190
中国科学院大学 工程科学学院,北京 100049 
谭春青 中国科学院 工程热物理研究所,北京 100190
中国科学院大学 工程科学学院,北京 100049 
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中文摘要:
      以级压比为4.1的Krain叶轮为研究对象,数值研究流量、转速和叶顶间隙对叶顶泄漏涡(TLV)轨迹和主流/叶顶泄漏流交界面(ITLMF)位置的影响。数值结果表明:流量减小、转速升高和叶顶间隙减小,使叶顶泄漏涡轨迹远离吸力面、主流/叶顶泄漏流交界面向上游移动。将主流与叶顶泄漏流的相互作用简化为一股自由来流与一股逆向壁面射流的相互作用,并对叶顶泄漏流速度进行模化。利用主流/叶顶泄漏流动量平衡原则确定交界面位置,采用Zhao模型预测叶顶泄漏涡轨迹,并建立叶顶泄漏流的有效起始位置与叶顶间隙的关系,从而建立亚声速离心压气机失速预测模型。结果表明,模型预测值与CFD预测值符合较好,方均根误差低于2.42%。
英文摘要:
      The Krain impeller with total pressure ratio of 4.1 was taken as the research object. The effects of mass flow rate, rotational speed and tip clearance on the tip leakage vortex (TLV) trajectoryand the interface between the tip leakage flow and the main flow (ITLMF) were numerically investigated. Results showed that the decrease of mass flow rate, the increase of the rotational speed and the decrease of the tip clearance made the TLV trajectory move away from the suction surface and the ITLMF move upstream. By simplifying the main flow and tip leakage flow interaction as the free-stream and counter-flow wall jet interaction, a subsonic centrifugal impeller stall-onset prediction model was developed. In this model, the momentum balance analysis was applied to identify the position of main flow/tip leakage flow interface. The tip leakage flow velocity was modeled. Zhao’s model was used to predict the TLV trajectory. The relationship between the virtual origin of tip clearance jet and the tip clearance was determined. Results showed that the stall point predicted by current model agreed well with CFD, with the root mean square error was below 2.42%.
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