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《Fluid Machinery》 2010-08
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Investigation on the Performance Prediction of Single-Stage Axial Compressor by Using Different Turbulence Models

WANG Yi-tian1,2,ZHANG Zhao-lei1,XU Jing2,WANG Dong2,HUANG Shu-jian1 (1.School of Power and Energy Engineering of Xi'an Jiaotong University,Xi'an 710049,China;2.Shanxi Blower(group) Co.,Ltd.,Xi'an 710075,China)  
The Numerical Simulations of the steady flow were performed by using Spalart-Allmaras,k-ε,k-ω,BSL,SST and ω turbulence models in the single-stage axial compressor at different flow rates.The predicted overall performances were compared to the reliable experimental data.The results show that relatively accurate predictions can be obtained at,or close to,the design point,but the reliability of the predictions was questionable at off-design conditions,especially near the stall point and chock point.Therefore,an investigation was achieved to find out the cause of the deviations by analyzing the pressure coefficient,polytropic effecinecy,pressure ratio as well as difference in temperature.The reason was that the viscous losses of the flow were underestimated in the turbulence models,especially near the stall point and chock point.In the six turbulence models,the k-ω model has more accuracy with large predictable operation range and less CPU time,and Spalart-Allmaras model saves CPU time but less accurate.
【Key Words】: turbulence model numerical simulation axial compressor performance prediction
【CateGory Index】: TH453
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【Citations】
Chinese Journal Full-text Database 3 Hits
1 SU Xin-Rong YUAN Xin Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Tsinghua Univ., Beijing 100084, China;NUMERICAL OVERALL PERFORMANCE CALCULATION OF MULTISTAGE AXIAL COMPRESSOR[J];Journal of Engineering Thermophysics;2006-02
2 CHENG Rong-hui1,2,LEI Pi-ni2,LIU Bo3,ZHOU Bai-hao2,ZHOU Sheng1(1.School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing 100083,China;2.Gasturbine Establishment of China,Chengdu 610500,China;3.School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China);A two-dimension numerical method for multi-stage axial compressor performance in engineering applications[J];Journal of Aerospace Power;2007-06
3 SHAO Wei-wei1,2,JI Lu-cheng1,CHEN Jiang3(1.Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100080,China; 2.Graduate School of Chinese Academy of Sciences,Beijing 100049,China; 3.School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing 100083,China);Two-dimensional Performance Prediction Method of Axial Compressor for Stall Margin Customizing[J];Gas Turbine Experiment and Research;2006-02
【Co-citations】
Chinese Journal Full-text Database 1 Hits
1 YIN Song,JIN Dong-hai,ZHU Fang,GUI Xing-min(School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China);Numerical simulation of the performance of a four-stage fan[J];Journal of Aerospace Power;2010-06
【Secondary Citations】
Chinese Journal Full-text Database 5 Hits
1 ZHANG Shi-Jie; YUAN Xin; YE Da-Jun (Dept. of Building Science, School of Architecture, Tsinghua Univ., Beijing 100084, China; Dept. of Thermal Engineering, Tsinghua Univ., Beijing 100084, China);NUMERICAL SIMULATION OF THE OVERALL AERODYNAMIC PERFORMANCE OF MULTI-STAGE AXIAL-FLOW COMPRESSOR[J];Journal of Engineering Thermophysics;2002-02
2 LIN Zhi-Rong YUAN Xin(Department of Thermal Engineering, Tsinghua University, Beijing 100084, China);PARALLEL COMPUTATION OF THREE-DIMENSIONAL FLOW FIELD WITHIN TURBOMACHINERY[J];Journal of Engineering Thermophysics;2002-06
3 Hu Jun (2nd Dept.Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China);Calculation of off Design Performance of Multistage Compressors with Uniform and Radial Distorted Inlet Flow[J];JOURNAL OF AEROSPACE POWER;2000-03
4 CHENG Rong-hui(China Gas Turbine Establishment,Chengdu 610500,China);Development of Design Technology for Axial Compressor[J];Gas Turbine Experiment and Research;2004-02
5 GAO Xue-lin, LIN Zhi-rong, YUAN Xin(Dept. of Thermal Engineering, Tsinghua University, Beijing 100084, China);Calculation of the Overall Aerodynamic Performance ofMultl-Stage Axial-Flow Compressor[J];Thermal Turbine;2004-03
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