航空发动机供回油流路流动换热数值仿真

Numerical Simulation of Flow and Heat Transfer on Lubricant Supplying and Returning Flow Path of an Aero-engine Lubrication System

为得到某航空发动机润滑系统的供回油流路在发动机最大工作状态下的流量分配和温度分布,采用GASLS系统对该流路进行了数值仿真。经过结构分析,构建了该供回油流路由仿真元件与节点组成的网络仿真模型。对流路中的轴承腔和换热器两类复杂部件,为降低整体网络的复杂度,分别对其独立进行仿真分析得到其工作特性,然后以组合仿真元件形式代入供回油流路的整体仿真网络进行计算。在给定的试验条件下,采用一维网络算法,得到稳态情况下供回油流路关键节点处的流量、压力和温度分布。最终的仿真分析结果与试验参考值吻合较好。

For the purpose of getting lubricant flow flux and temperature distribution of a lubricant supplying and returning flow path in an aero - engine lubrication system under the maximum power condition, a simulation model made up of elements and nodes is presented in GASLS software system. Based on the structure topology analysis of the flow path system, the bearing bores and heat exchangers are separated from the system and simulated to get their working characteristics. And they are substituted as combined elements to the whole network to reduce the simulation complexity. Final simulation model is analyzed by an one - dimensional steady state network algorithm under the test conditions and the lubricant flow flux, pressure and temperature at the key nodes are calculated. The simulation resuits show good agreement with experimental data.