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组合叶栅的定义及其应用研究 被引量:2

Research on the Combined Cascade
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摘要 提出了组合叶栅设想及其评价准则 ,并对组合叶栅进行了性能实验。通过实验数据的分析 ,肯定了组合叶栅设想应用于可逆风机叶片设计的可行性。实验还证明 ,选取适当的叶栅组合参数 B、T,可以使组合叶栅的整体性能得到大幅度的改善 ,与现有的翼型相比 ,CN + Ry max、αN + In this paper,a new design,named combined cascades,which is applied to blade design of reversible axial fan,is put forward based on the assimilating of the previous experience,the advanced technology and the up to date thinking.A new criterion for judging the blade performance in reversible axial fan is presented.NACA0012 airfoil is singled out as the experimental airfoil of the combined cascades.In the two dimensional wind tunnel experiment,the comprehensive performance of the combined cascades is understood through analyzing pressure contours of both the blades and substantive data got from inlet and outlet of cascade at the different overlap ratios,pitch ratios and attack angles.Based on analyzing and comparing results gotten from experiment,it is found that the aerodynamic characteristic of combined cascades is superior to any other cascades.Compared with S type airfoil,which is specifically designed for reversible axial fan,maximum lift coefficient C N+R y max of the symmetrical combined cascades is improved by about 20% and the stall attack angle α N+R C y max about 23 5%.And with NACA0012 single cascade,lift coefficient increases by 8 46% and the stall attack angle 17 5%.The unique flow rules of the combined cascades are understood through analyzing data.The flow in the combined cascades must meet the flow prerequisite i.e.the static pressure must be equivalent along the pitch wise at the outlet of the fan.The overlap ratio B is the one of the most important parameters by which the relative position of two rows of cascade could be determined.As B is chosen within 30%~50%,two rows could be operated respectively at their own stall attack angles and the cascade performance could be improved obviously.The pitch ratio T is another important parameter and could effect cascade performance directly.The smaller T is more suitable to the cascade performance and the optimum range should lie in between 40% and 50%.
出处 《航空动力学报》 EI CAS CSCD 北大核心 2002年第3期309-313,共5页 Journal of Aerospace Power
关键词 定义 组合叶栅 风洞实验 翼型 叶片设计 栅距比 combined cascade wind tunnel experiment airfoils
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参考文献4

二级参考文献7

  • 1魏百锁,1989年
  • 2赵德文,1989年
  • 3Li Longhua,1987年
  • 4匿名著者
  • 5Li Longhua,1987年
  • 6匿名著者,风机技术,1985年,67卷,3期,24页
  • 7伍金荣,风机技术,1981年,45卷,5期,8页

共引文献14

同被引文献28

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二级引证文献7

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