超燃冲压发动机内流性能的一维评估

One-dimensional evaluation of the scramjet flowpath performance

在准一维Eu ler方程的基础上,通过增加反映面积变化、摩擦、添质和化学反应放热的源项,发展了超燃冲压发动机推进流道计算的一维软件,可以在很短的时间内提供发动机的推力和摩擦力,同时给出发动机参数沿轴向的变化和出口值。通过日本国家航空与航天实验室(NAL)的双模态模型氢反应流场计算验证了软件的可靠性后,针对煤油发动机,分析了隔离段和燃烧室扩张角、燃料喷射位置与方式、化学反应放热项的两种不同求解方法、隔离段高度对燃烧室性能的影响,为飞行器设计配备了能稳定激波且性能较好的发动机构型。

One-dimensional code for the computation of the scramjet flowpath is developed by adding the source terms for the area variation, friction, mass addition and chemical heat release to the quasi-one-dimensional Euler equations. The thrust and friction forces as well as the parameters variations along the axis direction and the exit parameters of the scramjet were given in a short time. Validated by the computation of the reacting flow of NAL＇s dual mode seramjet model, the influences of the expanding angles of the isolator and the combustor, the location and the means of the fuel injection, the two methods to solve the chemical heat release term, the isolator height to the performance of the seramjet fueled by kerosene are analyzed. The scramjet configuration with good performance with steady shock for the flying vehicle design can be demonstrated.