氧化剂气量配比对Mg/CO2发动机性能影响实验

基于国内外粉末火箭发动机的研究基础以及工业上粉体燃烧器设计方法，提出了一种Mg/CO2粉末火箭发动机构型和氧化剂气体分3次进气的燃烧组织方案，并针对其工作过程开展了实验研究。主要研究了在氧燃比为4∶1条件下，氧化剂不同进气方案时发动机的燃烧效率和燃烧室内沉积情况，从而为后续的Mg/CO2发动机多次起动实验工况参数设定提供依据。发动机热试实验结果表明:当燃烧室头部氧燃比较大时，发动机稳焰失败，无法正常工作；发动机热试实验中燃烧效率最高为64.0%；当氧化剂进气方案满足流化气、旋流气与侧向气量配比为2∶0.5∶1.5时，燃烧室内基本无沉积。 

Experiments on influence of oxygen gas intake plan on performance of Mg/CO2 engine

A type of Mg/CO2 powder rocket engine configuration and a combustion organization plan with three times intake of oxidant gas were put forward based on the research of powder rocket engines at home and broad as well as the design methods of powder burners in industry. Experimental researches on its working process were carried out. The engine combustion efficiency and chamber deposit were studied under different oxygen gas inlet plans under the oxygen to fuel ratio 4∶1, so as to provide the basis for setting the parameters of Mg/CO2 powder rocket engine multiple-start working conditions. The engine hot-experiment results showed that the flame failed to keep stable and the engine can not work normally when the oxygen to fuel ratio in combustion chamber head was too large. The highest combustion efficiency was 64.0% among all hot experiments. There were almost no deposits in combustion chamber under the oxygen gas intake plan when the amount ratio of fluidization gas, cyclone gas and lateral gas was 2∶0.5∶1.5.