涡扇发动机叶片包容性与转子不平衡试验  

Test on Engine Containment and Rotor Unbalance of Turbofan Engine

作　　者：张清 沈锡钢 徐丹 陈萌 ZHANG Qing;SHEN Xigang;XU Dan;CHEN Meng(AECC Shenyang Engine Research Institute Shenyang,110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《振动．测试与诊断》2024年第6期1144-1151,1247,共9页Journal of Vibration,Measurement & Diagnosis

基　　金：航空动力基础研究资助项目;国防科技重点工程资助项目。

摘　　要：为研究某型大涵道比涡扇发动机叶片包容性和转子系统抗不平衡能力,开展了风扇叶片飞失后的机匣包容性和转子不平衡试验方法研究及验证。首先,采用在断裂叶片根部预置炸药断裂叶片的试验方法,应用设计的试验系统,在规定的发动机转速下,通过遥控爆破炸药技术实现1片风扇叶片在预定位置断裂;其次,高速摄像从不同方位记录了试验过程;最后,专项参数测量系统获得了非线性瞬态动力学响应结果。结果表明:叶片飞失后引起损伤叶片约为1.48个,均沿发动机进口或尾喷口轴向飞出,满足机匣包容要求;叶片飞失瞬间对机匣和转子系统产生了超过1000g的冲击载荷,转子传力路线上的承力结构完整,安装系统连接稳定,转子不平衡载荷引起低压转子支点轴承座与承力机匣连接螺栓丧失锁紧功能;发动机在引爆炸药后18 s停车。试验结果满足相关条款要求,验证了某大涵道比发动机叶片包容与转子不平衡的适航符合性。In this study,the test methods of casing containment and rotor unbalance after the loss of fan blades are explored and verified following the tests to reveal the blade inclusiveness and rotor system unbalance ability of a turbofan engine with high bypass ratio.With the test method of preset explosive fracture blade at the root of the fracture blade and the designed test system,the fan blade is broken at the predetermined position by remote control blasting explosive technology at the specified engine speed.The test process is recorded by the highspeed camera from different directions,and the nonlinear transient dynamic response results are obtained by the special parameter measurement system.The number of damaged blades caused by blade loss is about 1.48,all of which fly out axially along the engine inlet or tail nozzle.This satisfies the casing containment requirements.Additionally,the instantaneous impact load on the casing and rotor system is more than 1000g.The loadbearing structure on the rotor force transmission line is complete,and the installation system is stable.Owing to the unbalanced load of the rotor,the low-pressure rotor fulcrum bearing loses the locking function of the connecting bolt with the load-bearing casing.The engine stops 18 seconds after detonating the explosive.Test results meet the requirements and demonstrat that the airworthiness of the blade containment and rotor unbalance of a high bypass ratio engine are consistent.

关 键 词：涡扇发动机 风扇叶片飞失 包容试验 转子不平衡 适航符合性 

分 类 号：TH114[机械工程—机械设计及理论] V216.57[航空宇航科学与技术—航空宇航推进理论与工程]