论文部分内容阅读
针对进排气系统与燃烧室匹配工作的中心支板式火箭基组合动力循环(RBCC)发动机,通过数值模拟研究了RBCC发动机在低动压、高速高空域飞行条件下以超燃/火箭模式工作时的燃烧流场特征,并分析了支板火箭喷管出口流量的变化对燃烧流场的影响。结果表明:在超燃/火箭模式下,支板火箭工作能促进燃料与空气的掺混燃烧,实现发动机稳定工作,同时可提升发动机的推力性能;随着支板火箭流量的增加,发动机产生的总推力逐渐增大,总推力与火箭流量大小近似成正比;随着火箭流量的增加,燃烧室中的流动状态向以超声速流动占主导地位发展,进气道的抗反压能力得到提升。
The RBCC engine is used to match the intake and exhaust system with the combustion chamber. The RBCC engine is operated under the condition of low dynamic pressure and high-speed high-altitude flight in the super-combustion / rocket mode by numerical simulation The characteristics of the combustion flow field are analyzed. The influence of the change of the outlet flow rate on the combustion flow field is analyzed. The results show that under the scramjet / rocket mode, the supporter rocket works can promote the blending combustion of fuel and air to achieve stable engine operation and enhance the thrust performance of the engine. As the rocket flow rate increases, The total thrust force increases gradually, and the total thrust force is proportional to the rocket flow rate. With the increase of the rocket flow, the flow state in the combustion chamber dominates with the supersonic flow, and the anti-back pressure capability of the intake port is enhanced.