双模态超燃冲压发动机流量匹配的临界面积法

建立基于控制体法的0-D守恒方程(流量连续方程、动量守恒方程和能量守恒方程)的热力喉道(Ma=1.0)求解集总参数模型,该模型包括了壁面摩擦模型、燃油喷射模型、燃油雾化掺混模型和化学动力学模型.并针对集总参数模型求解热力喉道的特殊性,提出了基于流量平衡的临界面积法,应用于隔离段和燃烧室的1-D流场计算,实现了双模态超燃冲压发动机具有热力喉道时的各种模态的隔离段和燃烧室的流量平衡计算,精确捕捉到热力学喉道,确定了隔离段流动状态和燃烧室的工作模态及相关的流路沿程参数.计算结果表明:采用了临界面积法的集总参数计算模型能解决热力学喉道求解问题,其计算精度达10-4,单点工况计算时间小于0.1s.

Critical area method for mass flow matching of dual-mode scramjet

The lumped parameter model for thermo-throat (Ma=1.0) simulation was established based on 0-D conservation equations(continuity equation,momentum conservation equation and energy conservation equation) of the control volume,including:wall friction model,fuel injection model,fuel atomization and mixing model,and chemical kinetics model.To solve the problems in simulating the thermo-throat with lumped parameter model,a critical area method based on mass flow balance was proposed to simulate the 1-D flow field of the combustor.With this method,the mass flow balance between isolator and combustor in different modes when a dual-mode scramjet worked in thermo-throat condition was achieved,and the thermo-throat was accurately captured;in addition,the isolator flow state,the combustor operation modes and the flow path parameters were determined.The results show that the lumped parameter computation model with the critical area method can solve the problems in thermo-throat simulation,its computing accuracy reaches 10^-4,and the computing time at every working condition is less than 0.1s.