火箭发动机出口参数对喷焰流动及辐射的影响

基于详细化学反应机理+逐线积分法+视在光线法开展了火箭发动机喷焰流动与辐射特性研究,分析了不同化学反应机理对流动与辐射的影响,利用地面试验数据校验了模型的正确性,并详细分析了火箭发动机出口参数变化对喷焰流动及辐射的影响规律。研究结果表明:喷管出口温度增加,对流场结构影响较小,但会显著提升喷焰的复燃效应;喷管出口压强增加,会对流场马赫波系结构产生影响,但对喷焰二次燃烧影响较小;喷焰红外辐射强度会随着出口温度或出口压强的升高而增加,且红外辐射强度与出口推力正相关。 

Influence of rocket engine exit parameters on flow and radiation characteristics of exhaust plume

Based on the detailed chemical reaction mechanism, the flow and radiation of the plume were studied by the method of computational fluid dynamics (CFD) + line-by-line integration and light of sight method. The effects of different chemical reaction mechanisms on flow and radiation were compared and analyzed. The validity of the model was verified by optical measurement data. On this basis, the influence of rocket exit parameters on plume flow and radiation was analyzed in detail. The results showed that: the temperature of the nozzle exit had little effect on the structure of the flow field, but had a significant effect on the afterburning; the increase of pressure at the nozzle exit had an effect on the wave structure of the Maher disk, but had little effect on the afterburning; the infrared radiation intensity of the plume increased with the increase of the temperature and pressure of the nozzle exit, and the infrared radiation intensity was positively related to the thrust of the engine.