论文部分内容阅读
根据某大型固体火箭发动机在地面试车喷管扩散段前部的烧穿故障的诊断，认为喷管的内型面半径对轴线的导函数在型面衔接点处不连续是导致烧穿故障的直接原因，通过对比模拟试验得到证实。又通过对原型喷管的N－S方程计算，发现在型面衔接处有漩涡存在，与最初分析的速度转折点的道理相一致，从而确诊故障。最后，提出型面设计的改进建议，即以余弦曲线代替圆弧曲线，使衔接点处导函数连续，可大大减弱冲刷烧蚀作用，从而避免烧穿。
According to a large solid rocket engine in the ground test the front of the diffuser section of the burning test wear and tear breakdown that the inner radius of the nozzle inner surface of the conduction function of the axis at the junction of the discontinuity is the result of burn-through failure The reason is confirmed by comparative simulation. Through the calculation of the N-S equation of the prototype nozzle, it was found that there was a vortex at the junction of the profiles, consistent with the rationale of the initial analysis of the speed turning point, so as to confirm the fault. Finally, the improvement proposal of surface design is put forward, that is to replace the arc curve with the cosine curve so as to make the conduction function at the convergence point continuous, which can greatly reduce the erosion ablation effect and avoid the burn-through.