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非对称来流下带隔板的二维短隔离段研究 被引量:12

Investigation for two-dimensional short isolator with a spacer under a asymmetric incoming airflow
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摘要 在隔离段中放置隔板,可以在满足气动性能的前提下缩短隔离段的长度。采用数值计算的方法对带隔板的二维隔离段与不带隔板的隔离段性能进行了比较,对非对称来流条件下不同进口附面层厚度隔离段内弯曲隔板的形状进行了研究,给出了非对称来流条件下隔离段内弯曲隔板的设计参数。结果表明,在进口马赫数为2,隔离段进口下板附面层厚度δ/H=0.24,上板附面层厚度为0时,通过放置弯曲隔板,在进出口压比相同与出口总压恢复系数基本不变的情况下,隔离段长高比减小了33%。 In order to reduce the length of the isolator without loss in efficiency, a method of putting the spacer in the isolator was applied. Computational fluid dynamics simulations were performed on the isolator with straight or curve spacer. Inflow conditions was supersonic flow with Mach 2. Under asymmetric incoming airflow, the effect of the curve spacer configuration on isolator performance was investigated. Design parameters for curve spacer design were given. The computational results indicate that the overall length could be reduced by 33 per cent without loss in static and total pressure recovery when the lower wall boundary layer thickness δ/H was equal to 0.24 and the upper wall boundary layer thickness δ/H was zero at the isolator entrance.
出处 《推进技术》 EI CAS CSCD 北大核心 2006年第1期66-70,共5页 Journal of Propulsion Technology
基金 国家"八六三"基金(2003AA723020) 南京航空航天大学博士学位论文创新与创优基金(4003-019002)
关键词 超燃冲压发动机 隔离段 弯曲隔板 流场 数值分析 Supersonic combustion ramjet engine Isolator Curve spacer Flow field Numerical analysis
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参考文献9

  • 1Sullins G A.Demonstration of mode transition in a scramjet combustor [J].J.Propulsion and Power,1993,9 (4).
  • 2Gustafson M D,Gruber M R.Isolator pressure rise correlations compared with new experimental data[C].ISABE,No.99-7135,1999.
  • 3Neumann E P ,Lustwerk F .High - efficiency supersonic diffusers[J] .J.Aeronautical Sci.,1951,18:369 ~ 374.
  • 4Cox-Stouffer S K,Hagenmaier M A.The effect of aspect ratio on isolator performance [C].AIAA 2001-0519.
  • 5Siegfried H Hasinger ,David K Miller.Two - dimensional supersonic diffuser experiments [J].AIAA J,1975,13(4).
  • 6Rodriguez C G .Asymmetry effects in numerical simula -tion of supersonic flows with upstream separated regions[C].AIAA 2001-0084.
  • 7Carroll B F,Dutton J C.Computations and experiments for a multiple normal-shock/boundary-layer interaction[J].J.Propulsion and Power,1993,9 (3).
  • 8Waltrup P J,Billig F S.Structure of shock waves in cylindrical ducts [J].AIAA J.,1973,11 (10).
  • 9王成鹏,张堃元,金志光,李念.非均匀超声来流矩形隔离段内流场实验[J].推进技术,2004,25(4):349-353. 被引量:11

二级参考文献8

  • 1Waltrup P J, Billig F S. Structure of shock waves in cylindr ical ducts[J].AIAA J.,1973,11(10):1404-1408.
  • 2Carroll B F,Dutton J C.Characteristics of multiple shock wave/turbulent boundary-layer interactions in rectangular ducts[J].J. Propulsion and Powe r,1990,6(2):186-193.
  • 3Carroll B F, Dutton J C. Computations and experiments for a multiple n ormal-shock/boundary-layer interaction[J]. J. Propulsion and Power,199 3,9(3):405-411.
  • 4Lin P. Geometric effects on precombustion shock train in constant area is olators[R].AIAA Paper,93-1838,1993.
  • 5Gustafson M D,Gruber M R.Isolator pressure rise correlations compared wit h new experimental data[R].ISABE,99-7135,1999.
  • 6丁猛,李桦,范晓樯.等截面隔离段中激波串结构的数值模拟[J].国防科技大学学报,2001,23(1):15-18. 被引量:6
  • 7张堃元,王成鹏,杨建军,徐惊雷.带高超进气道的隔离段流动特性[J].推进技术,2002,23(4):311-314. 被引量:27
  • 8王成鹏,张堃元,杨建军.带进气道的隔离段流场实验研究与数值模拟[J].推进技术,2004,25(1):27-31. 被引量:12

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