摘要
为研究某型小涵道比带加力涡扇发动机加力接通对主机工作稳定性的影响,开展了试飞研究,分析了加力接通过程中出现的低压转子转速超限、风扇失速以及转速和排气温度波动明显等异常现象和原因。分析结果表明:加力接通过程中,加力燃油增加时尾喷口面积过度放大导致低压转子转速突增而超转;尾喷口面积放大不足使得风扇后压力急剧增高而导致风扇失速;加力点火后,尾喷口面积控制规律与加力油量不匹配会导致风扇后压力波动,进而主机参数和尾喷口面积随之波动。本文的研究成果对于涡扇发动机加力接通时出现的主机参数异常的原因分析、故障排除、试飞保障以及型号改进改型都具有重要价值。
In order to study the influence of reheat lit on the working stability of a small bypass ratio turbofan engine with afterburner,flight test research is carried out.The abnormal phenomena and causes of the over limit of the low pressure rotor speed,the fan stall,and the obvious fluctuation of the speed and exhaust temperature during the reheat lit process are analyzed.The results show that when the afterburner is connecting,the excessive enlargement of the nozzle area will lead to the sudden increase of the low pressure rotor speed and over rotation.Inadequate enlargement of the nozzle area makes the pressure behind the fan increase sharply,which leads to the fan stall.After afterburner ignition,the mismatch between the nozzle area control law and the afterburner oil volume will lead to the pressure fluctuation behind the fan,and then the main engine parameters and the nozzle area will fluctuate accordingly.The research results are of great value to the cause analysis,troubleshooting,flight test support,and model improvement and modification of the turbofan engine when the afterburner is connecting.
作者
张正元
Zhang Zhengyuan(Engine Department of Chinese Flight Test Establishment,Xi′an710089,Shaanxi,China)
出处
《工程与试验》
2022年第4期55-58,共4页
Engineering and Test
