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

• 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
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-07555678/
• 关键词: Supersonic Combustion; Hydrogen Combustion; Preburner; Numerical Simulation; Rich Combustion; Active Species; Strut; スクラムジェット; セラミックス; 保炎

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.

为了成功研制超音速推进装置，需要具备点火和火焰稳定方面的知识。由于这种装置内的流动是超音速的，与亚音速燃烧室中的情况相比，混合和反应时间大大减少。混合和反应时间显著缩短的一个直接含义是火焰稳定过程的敏感性增加，这表现在点火延迟的延长和散体火焰被熄灭或熄灭的更大倾向。本研究旨在首先利用预燃方法解决低马赫数超音速气流中的点火和火焰稳定问题。其次，研究了超音速气流中预燃氢气的燃烧机理和火焰结构。第三，了解预燃氢气在超音速气流中的火焰稳定性。第四，建立了超音速湍流燃烧的数值计算方法，对超音速气流中预燃氢气的燃烧进行了数值模拟和实验研究。这些研究主要涉及着火、火焰稳定、火焰结构和燃烧机理以及反应流动的数值方法。首先，预测了预燃法点火和阻燃的可能性。结果表明，预燃法大大降低了自燃的温度极限。此外，还研究了预燃器当量比、预燃器压力和超音速气流温度对火焰发展的影响。研究发现，这三个参数对火焰保持和燃烧发展均有显著影响。在此基础上，通过数值模拟和实验对预燃氢气的火焰稳定极限进行了预测。

项目成果

Sadegh Tabejamaat: "Numerical Study on the Effect of Model Scaling on Flame Stabilization in a Wake Flow Field" Proceeding of Second International-Symposium on Scale modeling. (1997)

Sadegh Tabejamaat：“尾流流场中模型缩放对火焰稳定性影响的数值研究”第二届国际缩放建模研讨会论文集。

T. Niioka, K. Terada, H. Kobayashi and S. Hasegawa: "Flame Stabilization Characteristics of Strut Devided into Two Parts in Supersonic Airflow" Journal of Propulsion and Power. 11. 112-116 (1995)

T. Niioka、K. Terada、H. Kobayashi 和 S. Hasekawa：“超音速气流中分为两部分的支柱的火焰稳定特性”《推进与动力杂志》。

Sadegh Tabejamaat: "Numerical Study on the Effect of Model Scaling on Flame Stabilization in a Wake Flow Field" Proceeding of Second International Symposium on Scale modeking. (1997)

Sadegh Tabejamaat：“尾流流场中模型缩放对火焰稳定性影响的数值研究”第二届国际缩放建模研讨会论文集。

M. Uchiumi, H. Kobayashi, S. Hasegawa and T. Niioka: "Flame-Holding Mechanisim of a Newly Devised Strut for Scramjet Engine" Transactions of the Japan Society for Aeronautical and Space Sciences. 38. 117-125 (1995)

M. Uchiumi、H. Kobayashi、S. Hasekawa 和 T. Niioka：“超燃冲压发动机新设计支柱的火焰保持机构”日本航空航天学会会刊。

Sadegh, Tabejamaat: "Numerical Simulation of Secondary Combustion of Hydrogen Injected from Preburner into Supersonic Airflow" AIAA Jounal. Vol.35. 1441-1447 (1997)

Sadegh, Tabejamaat：“从预燃器注入超音速气流的氢气二次燃烧的数值模拟”AIAA 杂志。