Shock-wave-induced mixing enhancement in scramjet combustors
Shock-wave-induced mixing enhancement in scramjet combustors
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DOI：
10.2514/6.1989-104
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发表时间：
1989
期刊：
影响因子：
--
通讯作者：
S. Menon
中科院分区：
文献类型：
--
作者：
S. Menon
为了确定激波诱导混合增强的可能性，对弱激波与超声速剪切层之间的相互作用进行了实验研究。超音速（马赫数2.5）的氮气流与音速氦气射流混合后向台阶下游，以模拟超燃冲压发动机火焰稳定器附近的混合区。一个小的楔形体被用来产生一个斜激波，冲击在混合层。进行了纹影流动显示和瑞利散射浓度测量。结果表明，剪切层的显着扩展可能发生在下游的激波/剪切层干扰区。需要进一步研究，以确定所观察到的扩散机制和混合效率提高的程度。由于存在激波诱导损失，在该方法能够在SCRAMJET燃烧室中得到验证和成功实施之前，必须确定最佳的混合增强配置。
An experimental study of the interaction between a weak shock wave and a supersonic shear layer was carried out to determine the possibility of shock-induced mixing enhancement. A supersonic (Mach 2.5) stream of nitrogen was mixed with a sonic helium jet downstream of a rearward-facing step to simulate the mixing region in the vicinity of a SCRAMJET flameholder. A small wedge was used to generate an oblique shock wave that impinges on the mixing layer. Schlieren flow visualization and Rayleigh scattering concentration measurements were carried out. The results indicate that significant spreading of the shear layer may occur downstream of the shock/shear layer interaction region. Further study is required to determine the mechanism of the observed spreading and the extent of the increase in mixing efficiency. Since there are shock-induced losses, an optimum mixing enhancement configuration will have to be determined before the method can be validated and successfully implemented in a SCRAMJET combustor.