航空活塞发动机爆震抑制方法  

Detonation Restraining Method of Aero Piston Engine

作　　者：孟现召[1] MENG Xian-zhao(Luoyang Beijiao Airport,Civil Aviation Flight University of China,Luoyang Henan 471000,China)

机构地区：[1]中国民用航空飞行学院洛阳北郊机场,河南洛阳471000

出　　处：《航空发动机》2022年第2期70-75,共6页Aeroengine

基　　金：中国民用航空飞行学院科学研究基金(CJ2018-04)资助。

摘　　要：某型航空活塞发动机在运行中多次发生爆震故障,已有研究认为该型发动机全油门燃油流量低于64 L/h是其爆震的主要诱因,但实践中将该型发动机全油门燃油流量增大至71.9 L/h后仍然有爆震故障出现,表明该型发动机的爆震并非单一诱因。为探索该型发动机爆震的可靠抑制方法,利用EGView软件分析典型故障例数据,查找可能的隐藏诱因并采用控制变量法进行实践测试,结果表明:发动机巡航转速偏低是该型发动机爆震的另一重要诱因,并证实了全油门偏富油对该型发动机的大功率爆震倾向具有抑制作用。根据实践测试结果提出控制该型发动机全油门燃油流量不低于66 L/h和发动机巡航转速不低于手册规定2500~2525 r/min(推荐按上限设置)的解决方案,经6万余飞行小时的实践验证表明该型发动机的爆震故障已被可靠解决。Detonation faults had occurred many times in the operation of an aero piston engine. It had been considered that the main cause of detonation was that the full throttle fuel flow of the engine was lower than 64 L/h. However,in practice,detonation faults still occured after the full throttle fuel flow of the engine was increased to 71.9 L/h,indicating that the detonation of the engine was not a single cause. In order to explore the reliable detonation restraining method of the engine,the typical fault case data were analyzed by EGView software,the possible hidden causes were found and the practical test was carried out by control variable method. The results show that the low engine cruise rotation speed is another important inducement of detonation,and it is confirmed that the rich fuel at full throttle can obviously restrain the tendency of high-power detonation of the engine. According to the practical test results,a solution is proposed to control the full throttle fuel flow of the engine not less than 66 L/h and the engine cruise rotational speed not less than 2500~2525 r/min(recommended to be set according to the upper limit)specified in the manual. The practical verification of more than 60,000 flight hours shows that the engine detonation fault has been reliably solved.

关 键 词：航空活塞发动机 爆震抑制 发动机巡航转速 全油门燃油流量 EGView软件 

分 类 号：V231.22[航空宇航科学与技术—航空宇航推进理论与工程]