期刊文献+

总流量及分流比对某型风扇/压气机性能的影响研究 被引量:1

On Predicting Effect of By-pass Ratio and Total Flux on Fan /Compressor Performance
在线阅读 下载PDF
导出
摘要 使用数值模拟方法研究了某型风扇/压气机组合体在不同总流量与分流比下的预估性能。程序框架使用改进的流线曲率法,通过基元叶片法+附面层修正+分流环效应三者耦合的方法,采用改良的损失与落后角模型,使计算结果更为精确,得出了总流量及分流比对某型风扇/压气机组合体性能的影响的一些结论。研究结果进一步证明了该方法对于存在内外涵道的风扇/压气机性能预估的有效性。 With an improved numerical method applied to the S2 stream-surface streamline curvature approach, researched the effects of by-pass ratio and total flux on fan/compressor performance and the influence of splitter lip and thickness of boundary layer on end wall were counted. Using the improved loss and deviation angle model, the more accurate results were carried out. Some of the conclusions on predicting effect of by-pass ratio and total flux on Fan/Compressor performance were obtained. The results further proved the validity of the method for the perform- ance forecast on the fan/compressor contains of the internal and external bypass.
出处 《科学技术与工程》 北大核心 2014年第12期292-297,共6页 Science Technology and Engineering
基金 国家自然科学基金重点项目(51236006)资助
关键词 风扇/压气机性能 总流量 分流比 fan/compressor performance total flux by-pass flow ratio
  • 相关文献

参考文献10

  • 1Von Backstrom T W, Hobson G V, Grossman B L, et al. Investiga- tion of the performance of a CFD-designed transonic compressor stage, 36th AIAA/ASME/ASEE Joint Propulsion Conference Huntsville, Alabama, 2000.
  • 2Gunn J, Martindale W R, Wagner D W. Performance evaluation of a transonic wind tunnel compressor. 17th Aerospace Ground Testing Conference, Nashville, TN,1992.
  • 3朱荣国.带分流环的s2流面流场线松弛计算方法与程序.工程热物理学报,1981;V2(3):253-255.
  • 4金东海,桂幸民.某涡扇发动机多级高负荷风扇/压气机气动性能数值模拟[J].航空动力学报,2011,26(5):1059-1065. 被引量:8
  • 5刘波,王强,王掩刚,高丽敏.分流环端部流场求解方法研究[J].机械科学与技术,2001,20(2):215-217. 被引量:6
  • 6刘波,王强.不同分流比下风扇/压气机组合体性能预估研究[J].西北工业大学学报,2001,19(3):349-352. 被引量:7
  • 7周新海.叶轮机械三元气动计算方法.西北工业大学讲义,1981.
  • 8Creveling H F, Carmody R H. Axial flow compressor computer pro- gram for calculating off-design performance ( Program IV ). NASA Contract Report CR-72427,1968.
  • 9Mellor G L, Wood G M. An axial compressor end-wall boundary layer theory. Journal of Basic Engineering, 1971:293-300.
  • 10赵学瑞,廖其尊.黏性流体力学.北京:机械工业出版社,1983.

二级参考文献15

  • 1张长生,王小莉.轴流压气机设计点流动损失的预估和分析[J].航空动力学报,1993,8(1):29-33. 被引量:5
  • 2刘波.分流环周围流场计算研究.西北工业大学科研报告[M].,1997,12..
  • 3吴望一.STOKES流动中连续奇点分布的分段抛物线近似[J].力学学报,1984,(3).
  • 4刘波.具有任意分流比的风扇/压气机性能预测.西北工业大学科研报告[M].,1997,12..
  • 5李存杰.涡喷(涡扇)发动机的数值模拟和数值试验技术.飞航导弹,1995,11(1):56-60.
  • 6Denton J D. The calculation of fully three dimensional flow through any type of turbomachine blade row[R]. AGARD LS 140,1985.
  • 7Chima R V, Yokota J W. Numerical analysis of three-dimensional viscous internal flows[R]. NASA TM-100878, 1988.
  • 8Hah C. Numerical study of three dimensional flow and heat transfer near the endwall of a turbine blade row[R]. AIAA-89-1689,1989.
  • 9Hah C, Loellbach J. Development of hub corner stall and its influence on the performance of axial compressor blade rows[J]. ASME Journal of Turbomachinery, 1999, 121(1):67-77.
  • 10Dawes W N. The simulation of three-dimensional viscous flow in turbomachinery geometries using a solution-adaptive unstructure mesh methodology[R]. ASME 91-GT- 124,1991.

共引文献15

同被引文献12

引证文献1

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