航空发动机燃油热管理系统仿真及试验验证

Simulation and experimental verification of aero-engine fuel thermal management system

为充分利用燃油作为热沉介质,发挥其最大效益,针对航空发动机燃油热管理系统开展了AMESim建模仿真及试验验证。结果表明,主泵出口燃油温升的仿真与试验结果误差最大为2.99℃,热回油温升的仿真与试验结果误差最大为6.81℃。发动机典型状态点下,燃油热管理系统热回油温度和喷嘴前温度的仿真与试验结果差异在5℃以内,仿真模型置信度较高。研究结果可为技术人员开展航空发动机燃油热管理系统方案设计和评估提供参考。

To make full use of fuel as thermal sink media,AMESim modeling and simulation of fuel thermal management system of aero-engine was done,and experiment was carried out.Comparing with the inlet temperature of fuel system,the maximum temperature rise error between experiment and simulation of the main pump outlet was 2.99℃,and that of heat return fuel was 6.81℃.For typical operation points of aero-engine,the error between experiment and simulation of heat return fuel temperature and temperature in front of nozzle was within 5℃,which indicated that confidence degree of the simulation model was high.The research provides reference for concept design and assessment of aero-engine fuel thermal management system.