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Experimental study on combustion characteristics of powder magnesium and carbon dioxide in rocket engine

机译：粉末镁和二氧化碳在火箭发动机中燃烧特性的实验研究

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摘要

Mechanisms of powder magnesium and carbon dioxide combustion are required for the concept of Mars propulsion based on the perspective of in-situ resource utilization. Most current characterizations are based on laboratory experiments conducted in stationary or simple flow configuration. However, the chamber condition in most applications of engine is very complicated with high pressure and multi-phase flow environment, and the combustion process in engine-scale has not been established. The burning efficiency, combustion stability and excessive deposition are the mainly primary issues that limit the combustion performance in rocket environment, the experimental study aims at combustion characteristics and the affection mechanism of powder magnesium and carbon dioxide in rocket engine. A new configuration of powder rocket system is established. Meanwhile, a multiple-inlet configuration of CO2 injection is designated to control the CO2 injection positions and parameters, such as global and local oxidant-fuel ratio. Ignition process is studied and an empirical model for ignition judgment is established according to the result of ignition tests. Mechanism for combustion deposition is studied by the analysis of morphology, composition and distribution, characteristics of combustion efficiency are estimated based on test pressure and thermodynamic calculation, and oscillation mechanism of combustion pressure is obtained by frequency domain analysis. The higher concentration of magnesium particle, the cool CO2 injection and the increasing of CO concentration is supposed to be the main reasons for the deposition in different areas along the axis of the combustion chamber. The allocation of gas injection is an important factor that affects the combustion sufficiency associated to the heterogeneous reaction. Raising the O/F ratio in chamber head is an effective way to improve combustion efficiency for rocket engine, and the efficiency is improved firstly and then is decreased with increasing flow rate of fluidization gas. The low frequency oscillation is supposed to be related to flame instability induced by the gas injection in chamber head. The influence caused by primary and secondary gas injection are further analyzed in the frequency domain, the related characteristic bands are classified and the fluctuation tendency is obtained.
机译：基于现场资源利用的观点，火星推进的概念需要粉末镁和二氧化碳燃烧的机制。当前的大多数特征是基于在固定或简单流动配置下进行的实验室实验。但是，在大多数发动机应用中，由于高压和多相流环境，燃烧室条件非常复杂，并且尚未建立发动机规模的燃烧过程。燃烧效率，燃烧稳定性和沉积过多是限制火箭环境下燃烧性能的主要问题，实验研究的目的是研究粉末镁和二氧化碳在火箭发动机中的燃烧特性及其影响机理。建立了粉末火箭系统的新配置。同时，指定了多个二氧化碳注入口配置来控制二氧化碳注入位置和参数，例如全局和局部氧化剂-燃料比。研究了点火过程，并根据点火试验的结果建立了点火判断的经验模型。通过形态，组成和分布的分析研究了燃烧沉积的机理，并基于试验压力和热力学计算，估算了燃烧效率的特征，并通过频域分析获得了燃烧压力的振荡机理。镁颗粒的较高浓度，冷的CO2注入和CO浓度的增加被认为是沿燃烧室轴线在不同区域沉积的主要原因。气体注入的分配是影响与多相反应相关的燃烧充分性的重要因素。提高燃烧室顶盖的O / F比是提高火箭发动机燃烧效率的有效途径，其效率先提高，然后随着流化气体流量的增加而降低。低频振荡被认为与由喷头注入室引起的火焰不稳定性有关。在频域上进一步分析了一次，二次气体注入的影响，对相关特征带进行了分类，得到了波动趋势。

著录项

  • 来源
    《Acta astronautica》 |2019年第2期|334-349|共16页
  • 作者

    Li Yue; Hu Chunbo; Zhu Xiaofei; Hu Jiaming; Hu Xu; Li Chao; Cai Yupeng;

  • 作者单位

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Shaanxi, Peoples R China|Northwestern Polytech Univ, Dept Astronaut, Xian, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Shaanxi, Peoples R China|Northwestern Polytech Univ, Dept Astronaut, Xian, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sci & Technol Combust Internal Flow & Thermal Str, Xian 710072, Shaanxi, Peoples R China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Magnesium; Carbon dioxide; Powder rocket environment; Powder propulsion; Combustion characteristics;

    机译：镁;二氧化碳;粉末火箭环境;粉末推进力;燃烧特性;

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