Transition of Combustion Mode in Scramjet

超燃冲压发动机燃烧模式的转变

基本信息

批准号：
13450394
负责人：
MASUYA Goro
金额：
$ 6.53万
依托单位：
Tohoku University
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (B)
财政年份：
2001
资助国家：
日本
起止时间：
2001 至 2002
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-13450394/
关键词：
Scramjet Dual Mode Combustion Pseudo-Shock Waves Mixing

项目摘要

Scramjet engines keep high performance in a wide Mach number range by shifling the combustion from the subsonic mode to the supersonic mode. This mode transition is a complicated interaction among mixing, combustion and pseudo-shock wave, and its detailed mechanism has not been clarified. This research project intends to clarify the transition mechanism by separating each phenomenon in the interaction and by controlling each phenomenon independently to investigate its influence to others.As the first step of the research, helium was injected into a supersonic flow produced by a suction-type wind tunnel. The pseudo-shock wave was produced and controlled by a back-pressure valve installed at the exit of the test section. The pseudo-shock wave strongly enhanced mixing of helium. The more upstream the pseudo-shock wave went, the stronger the enhancement effect became, The helium jet injected from the bottom wall of the test section usually spread in the lateral direction by the pseudo-shoc … More k wave, but the helium was diffused in the transverse direction depending on the location of the front of the pseudo-shock wave.In the second step, the back-pressure valve was removed and a plasma torch was attached as an injector. The feedstock of the torch was nitrogen or hydrogen/nitrogen mixture. The pseudo-shock wave was produced by increasing the input power to the torch and/or the fraction of hydrogen in the feedstock. It was found that the pseudo-shock wave was established when the generalized choking condition was satisfied at the exit section.When the front of the pseudo-shock wave went upstream about four times of the duct height from the injection port, the streamwise wall pressure distribution had a peak near the injection prot and decreased in the downstream direction. The shock train in the pseudo-shock wave was seen only upstream of the injection port fuel was injected upstream the plasma torch. These result indicated that the combustion mode shifted from supersonic to subsonic. The amount of heat release measured at the exit section was less than the value required for the thermal choking in the quasi-one-dimensional theory. The transition of the combustion mode resulted increase of the penetration of the injectant, but no significant change was observed in the hydrogen distribution and the combustiorn efficiency. Less

Scramjet发动机通过将混合物从亚音速模式转移到超音速模式，将高性能保持在广泛的马赫数范围内。这种模式过渡是混合，组合和伪震波之间的复杂相互作用，其详细机制尚未澄清。该研究项目旨在通过将相互作用中的每种现象分开，并独立控制每个现象以研究其对他人的影响，以阐明过渡机制。作为研究的第一步，将氦气注入了由脉动风隧道产生的超音速流中。伪冲浪波是由安装在测试部分出口处的后压阀产生和控制的。伪震波强烈增强了氦的混合。伪震浪的上游越上升，增强效果的强度越强，从测试部分的底墙注射的氦气射流通常会通过伪轴沿侧向散布的速度散布……氦气越多，但氦气在横向方向上的氦气差异很大注射。火炬的原料是氮或氢/氮混合物。伪震波是通过增加火炬的输入功率和/或原料中氢的比例来产生的。发现在出口部分满足广泛的窒息条件时，建立了伪震浪。当伪冲浪波的前沿从注入端口上游大约四次，而流向壁压力分布在注射蛋白蛋白prot附近具有峰值，并在下游方向下降。只有注射端口燃料上游的伪震浪中的冲击火车才能在等离子火炬上游。这些结果表明，燃烧模式从超音速转移到亚音速。在出口部分中测得的热量小于准二维理论中热窒息所需的值。燃烧模式的过渡导致注射渗透的渗透增加，但在氢分布和复合材料效率中未观察到显着变化。较少的