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主轴承腔作为航空发动机润滑系统油气两相流的重要区域,腔内的高温高压及其回油特性对润滑系统的性能都有很大影响。利用VOF数值计算模型对某航空发动机轴承腔简化模型内油气两相流进行数值计算,将两相之间表面张力作为源项添加到动量方程中,并依据实际情况添加壁面黏附模型,计算结果与现有实验数据符合良好。分析几种工作参数下润滑油相界面的差异及其原因,研究腔压及回油油气体积比随转子转速及润滑油流量的变化规律。结果表明:腔内的压力沿周向在出口处附近较低,并且随着转子转速或润滑油流量的增加而增大;回油孔出口处油气体积比随润滑油进口流量增加而增大;当润滑油进口流量一定时转子转速增大不利于回油。
The main bearing cavity serves as an important area for oil-gas two-phase flow in the aeroengine lubrication system. The high temperature and pressure in the cavity and its oil return characteristics have a great influence on the performance of the lubrication system. The VOF numerical model is used to calculate the oil-gas two-phase flow in a simplified model of aeroengine bearing cavity. The surface tension between the two phases is added as a source term to the momentum equation. The wall adhesion model is added according to the actual situation. The existing experimental data is in good agreement. The differences of lubricating oil phase interface under several working parameters and their causes were analyzed. The variation law of cavity pressure and oil-gas volume ratio of oil return with the rotor speed and oil flow were studied. The results show that the pressure in the cavity is lower near the outlet in the circumferential direction and increases with the rotor speed or the flow rate of lubricating oil. The volume ratio of oil to gas at the outlet of the oil return hole increases with the increase of the oil inlet flow rate. When the lubricant inlet flow rate increases the rotor speed is not conducive to return oil.