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为了揭示潜入式喷管对固体火箭发动机工作稳定性的影响,基于VKI(Von Karman Institute for Fluid Dynamics)模型发动机,利用大涡模拟数值方法与脉冲衰减法,计算分析了潜入式喷管对涡声耦合特性及喷管阻尼的影响。结果表明:在存在障碍物旋涡脱落的条件下,潜入式空腔能够加剧涡声耦合强度,继而诱发明显的压力振荡,含有潜入式空腔模型内的压力振幅是不含潜入式空腔模型下的4倍左右;潜入式喷管削弱了发动机的阻尼特性,无潜入式空腔的喷管阻尼比含潜入式空腔的喷管阻尼提高了8.6%左右,而且喷管阻尼随着潜入式空腔体积的增大基本呈线性减小趋势。潜入式喷管一般而言不利于发动机工作稳定性。
In order to reveal the influence of submerged nozzle on the working stability of solid rocket motor, based on the model VKI (Von Karman Institute for Fluid Dynamics) model engine, by using the large eddy simulation numerical method and the pulse decay method, Coupling characteristics and nozzle damping effects. The results show that under the conditions of vortex shedding, the submerged cavities can aggravate the vortex coupling strength and induce obvious pressure oscillations. The pressure amplitudes in the submerged cavity model are not included in the submerged cavity model About 4 times; submerged nozzle to weaken the damping characteristics of the engine, nozzleless submerged cavity nozzle damping than with submerged cavity nozzle increased by about 8.6%, and nozzle damping with submerged empty The cavity volume increases basically linear decreasing trend. Submerged nozzle is not conducive to the general work of the engine stability.