附件机匣出油口润滑油温度计算方法

附件机匣出油口温度是飞机发动机多种部件设计时所需的重要参数.机匣出油口润滑油的温度、机匣内部润滑油温度场的分布和机匣壳体散热量三者互为计算条件,给计算带来困难.推导了机匣壳体散热量的理论计算模型,研究了用有限元软件计算散热量的方法,此外应用迭代方法解决了机匣内润滑油温度场未知的问题,计算出机匣壳体的散热量,从而得到附件机匣温度场的分布和机匣出油口润滑油的温度.经验证:计算结果与经验值相符,经验值偏于安全.编制出的利用ANSYS结果数据库计算散热量的程序,能够计算形状和边界条件复杂以及各向异性导热体的散热量,与理论计算值相比该程序的计算误差小于1%.

Computation of Lubricant Temperature at Outlet of Accessory Gearbox

The lubricant temperature at the outlet of accessory gearbox is an important parameter required in designing many kinds of aeroengine components.The temperature and its field distribution and the heat dissipation through gearbox case are conditional on each other in computation,thus making the computation much more difficult.A theoretical computation model is deduced,and the process to compute the heat dissipation by a finite element software is studied.In addition,an iterative method is introduced to solve the problem of the temperature field that is unknown.Then,the temperature field distribution of the accessory gearbox and the temperature at its outlet are both given.It is proved that the computed results comply with the safety-oriented empirical valves.The software we developed on the basis of the result database of ANSYS to compute the heat dissipation is available to the heat dissipation of complicated shapes and boundary conditions as well as that of anisotropic thermal conductors.The error computed by the program is less than 1% in comparison with theoretical calculation.