一种提高后掠侧压式进气道流量系数的有效措施

金志光; 张堃元

一种提高后掠侧压式进气道流量系数的有效措施

南京航空航天大学能源与动力学院, 江苏南京 210016

基金项目: 国家“863”基金资助(2003AA723020)

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出版历程
- 收稿日期: 2005-08-30
- 修回日期: 2005-12-10
- 刊出日期: 2006-10-28

An efficient method for increasing mass flow capture ratio of a three-dimensional sidewall compression scramjet inlet

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 在一种双楔顶压、侧板中置的常规后掠侧压式进气道基础上通过减小顶板第二压缩角,引入圆弧压缩面设计了一种具有较高流量系数的进气道。利用Fluent商业计算软件对比研究了该进气道与常规进气道在Ma=6和Ma=4下的流动特征及性能。研究发现,新的改进措施能在几乎不降低进气道总压恢复系数的前提下大幅度提高流量系数:在Ma=6来流条件下,改进后的进气道流量系数为0.87,比常规进气道提高14.5%;在Ma=4来流条件下,流量系数为0.69,提高了19%。
- 航空、航天推进系统 /
- 超燃冲压发动机 /
- 高超声速进气道 /
- 侧压式进气道 /
- 高流量系数 /
- 数值仿真
Abstract: For a typical backward-sweep sidewall compression scramjet inlet with two ramps and mid-located sidewalls,a modified inlet with higher mass flow capture ratio was designed by reducing the second ramp angle and using circular arc compression surface.The flow filed was numerically simulated and comparisons were made between the modified inlet and the typical one at the free stream Mach number of 6 and 4.Numerical results indicate that most of the performance parameters of the modified inlet are obviously improved and the mass flow capture ratio is greatly increased by using the new method.At Mach 6 incoming condition,the mass capture ratio of the modified inlet was 0.87,which was 14.5 percent higher than that of the typical one;at Mach 4 incoming condition,the mass flow capture ratio was 0.69,19% percent higher than that of the typical one.
- aerospace propulsion system /
- scramjet /
- hypersonic inlet /
- sidewall compression inlet /
- high mass capture ratio /
- numerical simulation

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参考文献(6)

[1]	丁猛,梁剑寒,刘卫东,等.碳氢燃料超燃冲压发动机进气道与燃烧室匹配性能试验研究[J].航空学报,2005,26(1):27-31.Ding Meng,Liang Jianhan,Liu Weidong,et al.Experimental study on the interaction between inlet and combustor of hydrocarbon fueled scramjet[J].Acta Aeronautica et Astronautica Sinica,2005,26 (1):27-31.
[2]	Tetsuo Hiraiwa,Takeshi Kanda,Tohru Mitani.Experiments on a scramjet engine with ramp-compression inlet at Mach 8 condition[R].AIAA 2002-4129.
[3]	杨进军,张堃元,徐辉,等.双模态冲压发动机高超进气道的实验研究[J].推进技术,2001,22(6):473-477.Yang Jinjun,Zhang Kunyuan,Xu Hui,et al.Experiment study on supersonic inlet in dual-model scramjet[J].Journal of Propulsion Technology,2001,22(6):473-477.
[4]	金志光,张堃元.高超侧压式进气道马赫6高焓脉冲风洞实验[J].推进技术,2005,26(4):319-323.Jin Zhiguang,Zhang Kunyuan.Mach 6 testing of a generic sidewall compression scramjet inlet in the high-enthalpy impulse wind tunnel[J].Journal of Propulsion Technology,2005,26(4):319-323.
[5]	金志光,张堃元.带前体压缩的前掠侧压式进气道实验及数值研究[J].推进技术,2005,26(6):508-512.Jin Zhiguang,Zhang Kunyuan.Experimental and numerical investigation of a forward sweep sidewall compression scramjet inlet with forebody compression[J].Journal of Propulsion Technology,2005,26(6):508-512.
[6]	Goonko Y P,Latypov A F,Mazhul I I,et al.Structure of flow over a hypersonic inlet with side compression wedges[J].AIAA Journal,2003,41(3):436-447.