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高负荷跨音压气机叶尖间隙流动的数值分析与比较
引用本文:敬荣强,李泯江,桂幸民.高负荷跨音压气机叶尖间隙流动的数值分析与比较[J].航空动力学报,2003,18(6):827-831.
作者姓名:敬荣强  李泯江  桂幸民
作者单位:北京航空航天大学,能源与动力工程学院,北京,100083
基金项目:国家自然科学基金资助项目(50076001,50136010)
摘    要:利用自行开发的叶轮机三维数值模拟软件对高负荷跨音压气机ATS-2转子进行了带叶尖间隙的三维流动数值模拟,并与实验的结果进行了比较。结果表明,数值模拟得到的流场结构与实验结果一致。对粘性与无粘结果的比较显示,由泄漏流所产生的激波后阻塞区是由激波-漏流干扰所致,粘性的作用将削弱其面积和强度。随叶尖间隙增大,激波后阻塞区的径向和轴向尺度增大,压比、效率和流量下降。

关 键 词:航空、航天推进系统  跨音压气机  叶尖间隙流动  数值模拟
文章编号:1000-8055(2003)06-0827-05
收稿时间:2003/1/22 0:00:00
修稿时间:2003年1月22日

Numerical Analysis and Comparison of the Tip-Clearance Flow of a High-Loading Transonic Compressor
JING Rong-qiang,LI Min-jiang and GUI Xing-min.Numerical Analysis and Comparison of the Tip-Clearance Flow of a High-Loading Transonic Compressor[J].Journal of Aerospace Power,2003,18(6):827-831.
Authors:JING Rong-qiang  LI Min-jiang and GUI Xing-min
Institution:Beijing University of Aeronautics and Astronautics,Beijing100083,China;Beijing University of Aeronautics and Astronautics,Beijing100083,China;Beijing University of Aeronautics and Astronautics,Beijing100083,China
Abstract:A 3D numerical simulation software was developed to calculate the tip-clearance flow of ATS-2,a high-loading transonic compressor,and the results were compared with the experiments.The results of numerical simulation are in accordance with that of experiments.The comparison between the viscous and non-viscous simulations shows that the intensive blockage area is caused by shock-leakage flow interaction.The viscosity weakens the blockage area,both in size and intensity.With the increase of the tip-clearance,the blockage area grows in the radial and axial directions with the total pressure ratio,efficiency and mass flow decreasing.
Keywords:aerospace propulsion system  transonic compressor  tip-clearance flow  numerical analysis
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