自燃推进剂火箭发动机燃烧不稳定性研究(英文)  

Hypergolic propellant rocket engine combustion instability studies

作　　者：聂万胜[1] 庄逢辰[1] 

机构地区：[1]装备指挥技术学院,北京101416

出　　处：《推进技术》2000年第4期63-65,76,共4页Journal of Propulsion Technology

摘　　要：发展了自燃推进剂 (MMH/NTO)火箭发动机燃烧不稳定性的综合分析模型。以蒸发作为燃烧速率控制过程 ,研究了燃烧不稳定性的机理。提出了轴向声腔模型并对其抑制不稳定燃烧的特性进行了数值模拟研究 ,得到了声槽特性频率对燃烧不稳定性的影响规律 ,描绘出声腔影响燃烧不稳定性的具体场景 ,数值模拟结果与理论分析及试车结果是相符的 ,对轴向声槽的分析设计将具有广泛的指导意义。A comprehensive model was developed for the analysis of MMH/NTO rocket engine combustion instability Fuel vaporization was identified as the combustion rate limiting process The mechanism for combustion instability was studied Axial acoustic resonator model was proposed and numerical treatment was developed Acoustic resonator characteristic frequency affecting the combustion stability was simulated numerically It was obtained on how axial slots affect combustion instability The frequency scope can be determined by the current method for the axial acoustic slots located at the outer edge of the injector Simulation results are agreeable to both the theoretical analysis and engine hot test data This is of great use to analyze and design liquid rocket engine

关 键 词：流体推进剂火箭发动机 自燃推进剂 燃烧稳定性 

分 类 号：V511[航空宇航科学与技术—航空宇航推进理论与工程] V434.13