Research and Development of Supersonic Combustion Strut with a Preburner

带预燃器的超音速燃烧支柱的研制

基本信息

批准号：
07555678
负责人：
NIIOKA Takashi
金额：
$ 2.11万
依托单位：
Tohoku University
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (A)
财政年份：
1995
资助国家：
日本
起止时间：
1995 至 1997
项目状态：
已结题

项目摘要

For the successful development of supersonic propulsion devices the knowledge of ignition and flame stabilization is needed. Since flows within such devices are supersonic, the mixing and reaction times are drastically reduced as compared to the situation within subsonic combustors. A direct implication of the significantly reduced mixing and reaction times is the enhanced sensitivity of the flame stabilization processes in terms of extended ignition delays and the greater propensity of the bulk flame to be extinguished or blown out.This study intends to first, solve the problem of ignition and flame stabilization in low Mach number supersonic airflow by using preburning method. Second, to investigate the combustion mechanism and flame structure of preburned hydrogen in supersonic airflow. Third, to understand the flame stability regime of preburned hydrogen in supersonic airflow. Fourth, to develop a numerical method for computation of supersonic turbulent combustion.Numerical and experimental studies on combustion of preburned hydrogen in supersonic airflow were done. These studies mainly were concerned with ignition, flame stabilization, flame structure and combustion mechanism as well as numerical method for reactive flows. First, the possibility of ignition and flame-holding by preburning method was predicted. It was shown that the temperature limit of auto-ignition is drastically reduced by using the preburning method. In addition, the effect of the preburner equivalence ratio the pressure of the preburner and the supersonic airflow temperature on flame development were studied. It was realized that each of these three parameters had significant effects on flame-holding and combustion development. Futhermore, flame stability limits of preburned hydrogen were predicted by numerical simulation as well as experiment.

为了成功地开发超音速推进设备，需要对点火和火焰稳定的了解。由于此类设备内的流量是超音速，因此与亚音速燃烧器中的情况相比，混合和反应时间大幅减少。显着减少的混合和反应时间的直接含义是，在扩展点火延迟方面，火焰稳定过程的灵敏度增强了，并且散装火焰的更大倾向被熄灭或吹走。这项研究打算首先解决问题，解决问题，解决问题。通过使用预燃烧方法，低马赫数超音速气流的点火和火焰稳定。其次，研究超音速气流中预燃烧的氢的燃烧机理和火焰结构。第三，以了解超音速气流中预燃烧的氢的火焰稳定性。第四，为了开发一种计算超音速湍流燃烧的数值方法。对超音速气流中预燃烧的氢的燃烧进行了数量和实验研究。这些研究主要与点火，火焰稳定，火焰结构和燃烧机制以及反应性流动的数值方法有关。首先，预测通过预燃烧方法点火和火焰持续的可能性。结果表明，使用预燃烧方法可以大大降低自动点燃的温度极限。此外，研究了预燃烧器等效比的影响，研究了预燃烧器和超音速气流温度对火焰发育的压力。人们意识到，这三个参数中的每一个都对火焰持续和燃烧的发展产生了重大影响。通过数值模拟和实验预测了预燃烧氢的火焰稳定性极限。