航空发动机轴承腔热状态分析模型及温度场计算

THERMAL ANALYSIS MODELS AND TEMPERATURE FIELD CALCULATION OF BEARING OIL CAVITY IN AN AEROENGINE

分析了轴承腔的主要热源。建立了轴承及石墨密封摩擦热的计算模型、密封热泄漏量的计算模型、对流换热系数的计算模型及温度场的计算模型。用热网络法建立了轴承腔的热平衡方程组，并采用拟牛顿法求解了该方程组。获得了１０种不同工况下的温度场计算结果，该结果与本文的测试结果基本吻合。

Endurance and reliability of an aeroengine and its bearings are closely related to the thermal state of thebearing oil cavity.The major heat sources which affect the thermal behavior of the bearing oil cavity in an aeroengine are analysed.The models for calculating bearing heat generation,graphite seal heat generation,heat leaking from the graphite seal,convection coefficients and temperature fields of the bearing oil cavity are established.The thermal balance coupled equations of the bearing oil cavity are derived from these models by thermal net method and are solved by quasi-Newtonian method.The steady state temperature fields of the bearing oil cavity are obtained from the solutions of 10 different operation conditions and are consistent with the experimental results in general.