摘要
采用自主研发的航空发动机滑油通风系统性能分析软件,对某型发动机通风流路进行了数值仿真。数值仿真以流动换热的网络算法为基础,经过结构分析,构建了通风流路仿真元件与节点组成的网络仿真模型。在给定实验条件下,数值仿真了稳态情况下通风流路腔室节点的压力,各密封装置泄漏量的分配。最终的仿真结果与实验参考值的误差在1%以内,验证了数值仿真方案的精度。
A simulation model is presented in a self- creating peribrmance analysis software of aeroengine vent system. The software adopts network algorithm. Based on the structure topology analysis, network simulation model is built which includes different elements and nodes. For validating precision of simulation, numerical calculation of the model is analyzed by a steady state network algorithm under the test conditions. The leaking flow flux of the seals and pressure at the key nodes of chamber are calculated. Errors between the simulation results and the experimental data are not beyond 1%, which validates the precision of numerical simulation.
出处
《航空计算技术》
2011年第4期32-35,共4页
Aeronautical Computing Technique
基金
西北工业大学科技创新基金项目资助(2009kj010006)
关键词
航空发动机
通风系统
仿真模型
网络算法
自定义元件
aeroengine
vent system
simulation model
network algorithm
self- defining element
