航空发动机刚性摇臂疲劳试验台设计及疲劳特性试验  

Design of rigid rocker arm fatigue test bench for aero engines and fatigue characteristics test

作　　者：顾志祥 曹传军 徐峰 孙文龙 龚文杰 张广辉[2] GU Zhixiang;CAO Chuanjun;XU Feng;SUN Wenlong;GONG Wenjie;ZHANG Guanghui(Commercial Aircraft Engine Company Limited,Aero Engine Corporation of China,Shanghai 200241,China;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]中国航发商用航空发动机有限责任公司,上海200241 [2]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《航空动力学报》2025年第1期306-314,共9页Journal of Aerospace Power

摘　　要：为了明确航空发动机刚性摇臂的疲劳特性,满足刚性摇臂在实际运行过程中要求,依托某型航空发动机设计了VSV机构刚性摇臂疲劳试验台,为模拟实际工况通过加载装置对等效叶片施加等效气动载荷,使用PID控制器控制作动筒行程并按照预设行程-时间曲线运行,在此工况下对刚性摇臂进行1000次疲劳循环,分析疲劳过程中叶片角度与机构阻滞力的变化,试验结果表明:左侧活塞杆阻滞力大于右侧活塞杆阻滞力,并且第1级连杆阻滞力要远小于其他各级阻滞力,同时验证了在进行1000次疲劳循环后叶片转动角度仍具备着较高精度。In order to clarify the fatigue characteristics of the rigid rocker arm of the aero-engine and meet the requirements of the rigid rocker arm during actual operation,a rigid rocker fatigue test bench of the VSV mechanism was designed based on a certain aero-engine.In order to simulate the actual working conditions,the equivalent aerodynamic load was applied to the equivalent blade by the loading device.The stroke of the actuator was controlled by PID and operated according to the preset stroke-time curve.The rigid rocker arm was subjected to 1000 fatigue cycles under the working condition,and the changes of blade angle and mechanism hysteresis force during the fatigue process were analyzed.The test results showed that the hysteresis force of the left piston rod was greater than that of the right one.The hysteresis force of the first stage connecting rod was much smaller than that of the other stages,and the blade rotation angle had higher accuracy after 1000 fatigue cycles.

关 键 词：疲劳试验台设计 刚性摇臂 疲劳试验 角度验证 阻滞力分析 

分 类 号：V233.5[航空宇航科学与技术—航空宇航推进理论与工程]