基于凹槽结构的泵喷推进器梢涡控制效果及计算方法

为了降低泵喷推进器的辐射噪声,借鉴航空发动机"处理机匣"技术,在泵喷推进器导管内壁上开设凹槽结构,达到降低泵喷推进器转子梢涡强度、抑制梢涡空化的目的。针对某型泵喷推进器,采用结构化网格,对比分析了无凹槽和有凹槽喷泵喷推进器的梢涡强度,结果显示,导管凹槽能够有效削弱梢涡强度;分析了湍流模型、网格数量和时间步长对计算结果的影响,初步建立了导管凹槽梢涡抑制效果的数值计算方法,研究结果为泵喷推进器梢涡控制提供了新的技术路径和技术支撑。

Research on the tip vortex control effect and calculation method of pump jet thruster based on groove structure

In order to reduce the radiation noise of pump jet thruster,the casing treatment technology of aero-engine is referenced and we add groove structures on the inner wall of the pump nozzle for the purpose of reducing the intensity and suppressing cavitation of tip vortex.We compare the intensity of tip vortex of pump jet thruster with groove between the one without groove by using structural mesh.Numerical tests demonstrate that duct groove can effectively weaken the intensity of tip vortex for a certain type of pump jet thruster.The influence of turbulence model,quantity of mesh,and time step on the calculating results is also analyzed and we establish numerical methods of suppression effect of tip vortex.The research can provide a new technological path and technical support for tip vortex control of pump jet thruster.