鱼雷燃烧室内衬压力平衡孔数值模拟研究

Numerical simulation of pressure balance hole in the torpedo combustion chamber lining

为提高鱼雷燃烧室在高温高压工作环境下的工作性能,基于热流固耦合数值计算方法,得到了鱼雷燃烧室内衬压力平衡孔的不同位置及大小对燃气域缝隙处流场及燃烧室内壳体强度的影响规律。计算结果表明:随着压力平衡孔与内衬上表面距离的减小,上方缝隙两端的压差减小、燃气流速降低、热通量变小,下方缝隙处的燃气流动几乎不受影响,内壳体的最大热应力值变小;随着压力平衡孔的增大,上方缝隙两端的压差先变小后变大、燃气流速先降低后增高、热通量先变小后变大,下方缝隙处的燃气流动几乎不受影响,内壳体的最大热应力值先变小后变大,且在孔径为4 mm时最小。由计算结果推断,鱼雷燃烧室内衬压力平衡孔最佳位置为距离内衬上表面30 mm处,孔径大小为4 mm。

In order to improving the working performance of the torpedo combustion chamber in high temperature and pressure, the effect laws of different positions and sizes of pressure balance hole in torpedo combustion chamber lining on the flow field at the gap of combustion area and the strength of the shell inside the combustion chamber were obtained based on the thermal-fluid-solid coupling method. The results indicated that, with decreasing the distance between the hole and the lining upper surface, at the top gap, the pressure difference between the two ends of the gap decreased, and the gas flow rate,heat flux and the maximum heat stress of the inside shell were reduced as well, but there were no effect on the combustion area and the shell at the bottom gap. With increasing the size of the pressure balance hole, at the top gap, the pressure difference between the two ends of the gap decreased first and then increased, and the gas flow rate, heat flux were also reduced first and then risen, but there were no effect on the combustion area and the shell at the bottom gap, and the maximum heat stress of the inside shell decreased first and then increased. Furthermore when the diameter was 4 mm, the maximum heat stress was minimum. It is inferred from the calculation results that the optimal location of the pressure balance hole is 30 mm from the upper surface of the lining and the optimal diameter is 4 mm.