小型航空发动机油雾润滑技术实验与数值研究

摘要

For 58.8 N thrust micro-engine W2P-6,the oil mist lubrication technology was investigated by experiment and numerical calculation.By changing the rotor speed and oil mist quantity and considering the influence of turbine wheel temperature,the variational trend of rotor bearings outer race temperature was investigated.Range of oil mist quantity which can ensure the rotor bearing working reliably at some speeds is found.Conclusions are drawn as follows：1） when the turbine wheel temperature influence is not considered,the front and the rear bearings outer ring temperatures increase with the rise of the simulated rotor speed;2） at the same speed,when the oil mist quantity is less than the design value,the temperatures of the front and the rear bearing outer ring are higher;3） when the oil mist quantity is bigger than the design value,the opposite is true;4） when turbine wheel place temperature influence is considered,it is discovered that when the rotor safely operates at the highest speed,the oil mist lubrication system needs about 4.8% air flow of the total engine flow;5） when the rotor work speed is reduced,the supply of the air would reduce accordingly.%针对推力为58.8 N的小型航空涡喷发动机W2P-6,进行油雾润滑技术实验与数值研究。对转子轴承外环温升随转速、油雾量的变化规律进行研究,同时研究了考虑涡轮温度影响的情况下,轴承外环温度随油雾量的变化规律,对若干转速确定一个能使轴承安全运转的油雾量范围。研究发现,不考虑涡轮温度影响时,模拟转子系统前、后轴承外环温度均随工作转速的升高而升高;在同一转速下,油雾量小于设计值时,模拟转子系统前、后轴承外环温度均比油雾量为设计值时的温度高,油雾量大于设计值时,则相反。考虑涡轮温度影响时,发现当涡轮处温度为400℃