期刊文献+

Flow Field Improvement by Bowed Stator Stages in a Compressor with Different Axial Gaps Under Near Stall Condition 被引量:4

变轴向间隙下压气机近失速工况时弯曲静叶改善流场的实验研究(英文)
下载PDF
导出
摘要 The outlet flow fields of a low-speed repeating-stage compressor with bowed stator stages are measured with five-hole probe under the near stall condition when the rotor/stator axial gap varies. The performances of the straight stator stages are investigated and compared to those of the bowed stator stages. The results show that using bowed stator stages could alleviate the flow separation at both upper and low corners of the suction surface and the endwalls, and decrease the losses along the flow passage as well as the outlet flow angle. As the rotor/stator axial gap decreases, although the diffusion capacity of the compressor increases obviously, the outlet flow field in the straight stator stages deteriorates quickly. By contrast, little changes occur in the bowed stator stages, indicating that as the rotor/stator axial gap decreases, improved performance is achieved in the bowed stator stages. The outlet flow fields of a low-speed repeating-stage compressor with bowed stator stages are measured with five-hole probe under the near stall condition when the rotor/stator axial gap varies. The performances of the straight stator stages are investigated and compared to those of the bowed stator stages. The results show that using bowed stator stages could alleviate the flow separation at both upper and low corners of the suction surface and the endwalls, and decrease the losses along the flow passage as well as the outlet flow angle. As the rotor/stator axial gap decreases, although the diffusion capacity of the compressor increases obviously, the outlet flow field in the straight stator stages deteriorates quickly. By contrast, little changes occur in the bowed stator stages, indicating that as the rotor/stator axial gap decreases, improved performance is achieved in the bowed stator stages.
出处 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2008年第3期215-222,共8页 中国航空学报(英文版)
基金 National Natural Science Foundation of China (50646021) Chinese Specialized Research Fund for the Doctoral Pro-gram of Higher Education (20060213007)
关键词 COMPRESSOR bowed stator rotor/stator axial gap near stall condition corner separation compressor bowed stator rotor/stator axial gap near stall condition corner separation
  • 相关文献

参考文献6

二级参考文献43

  • 1王顺杰,高军锋,薛荣亮.糖尿病患者述情障碍临床研究[J].临床心身疾病杂志,2006,12(5):354-355. 被引量:6
  • 2陈浮,陆华伟,顾中华,王仲奇.轴向间隙对压气机时序效应影响之一:总性能[J].工程热物理学报,2007,28(2):232-234. 被引量:13
  • 3杨琳,邹正平,李维,秦代斌.尾迹作用下不同负荷分布叶型边界层发展研究[J].工程热物理学报,2006,27(5):751-753. 被引量:8
  • 4Prince D C Jr, Wisler D D, Hivers D E.Study of Casing Treatment Stall Margin Improvement [R]. NASA CR134552,1974.
  • 5Takata H,Tsukuda Y. Stall Margin Improvement by Casing Treatment-It's Mechanism and Effectiveness [J]. ASME Journal Engineering for Power, 1977,99:121 ~ 133.
  • 6Crook A J,Greitzer E M,Tan C S, Adamczyk J J. Numerical Simulation of Compressor Endwall and Casing Treatment Flow Phenomena [J]. ASME Journal of Turbomachinery,1993,115:501~512.
  • 7Roberts F,Plourde G A,Smakula F. Insights into Axial Compressor Response to Distortion[R]. AIAA Paper 68~595.
  • 8Simon J,et al. The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading, Part Ⅰ and Part Ⅱ [J].AS M E Journal of Turbomac h iner y , 2002,124: 521 ~ 541.
  • 9Graf M,et al. Effect of Non-Axisymmetric Tip Clearance on Axial Compressor Performance and Stability[R]. ASME Paper 97-GT-406.
  • 10Spakovszky Z S,et al. Tip Clearance Actuation with Magnetic Bearings for High Speed Compressors Stall Control [R].ASME Paper 2000-GT-528.

共引文献43

同被引文献28

  • 1韩万金,杨庆海,黄洪雁,贾琳.Topology and Vortex Structures of Turbine Cascade with Different Tip Clearances[J].Chinese Journal of Aeronautics,2002,15(1):18-26. 被引量:5
  • 2张环,胡骏,李传鹏,王英锋.轴向间距对压气机气动稳定性的影响[J].航空动力学报,2005,20(1):120-124. 被引量:11
  • 3李传鹏,胡骏,吴铁鹰,王英锋.EFFECT OF AXIAL SPACING ON COMPRESSOR STABILITY[J].Transactions of Nanjing University of Aeronautics and Astronautics,2005,22(3):189-194. 被引量:1
  • 4张华良,王松涛,王仲奇.冲角对压气机叶栅内二次涡的影响[J].航空动力学报,2006,21(1):150-155. 被引量:18
  • 5Duquette M,Visser K D.Numerical implications of salidity and blade number on rotor performance of horizontal-axis wind turbines[J].Journal of Solar Energy Engineering,2003,125(4):425-432.
  • 6Wang S H,Chen S H.Blade number effect for a dueted wind turbine[J].Journal of Mechanical Science and Technology,2008(22):1984-1992.
  • 7H P Wang. Flow Visualization in a Linear Turbine Cas- cade of High Performance Turbine Blade [R]. ASME Paper 95-GT-7, 1995.
  • 8S Kang. Investigation of the Three Dimensional Flow Within a Compressor Cascade With and Without Tip Clearance [D]. Dept of Fluid Mechanics, Vrije Universiteit Brussel, 1993:I-1-V-44.
  • 9Hualiang Zhang, Songtao Wang, Zhongqi Wang. Varia- tion of Vortex Structure in Compressor Cascade at Differ- ent Incidences [J]. Journal of Propulsion and Power, 2007, 23(1): 221-226.
  • 10INOUE M, KUROUMARU M, YOSHIDA S, et al. Effect of tip clearance on stall evolution process in a low-speed axial compressor stage [ C ]//ASME Turbo Expo 2004 : Power for Land, Sea, and Air. Vienna,.

引证文献4

二级引证文献19

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部