Design of rigid rocker arm fatigue test bench for aero engines and fatigue characteristics experiment
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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。
Abstract: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 experiment 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.
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图 10 第100次循环各级叶片转动角度平均值
Figure 10. Average of blade rotation angle at each level in the 100th cycle
图 14 第100、400、500与1000次循环的活塞杆阻滞力
Figure 14. Piston rod drag force for 100th, 400th, 500th and 1000th fatigue cycles
图 16 第100次与第500次循环的连杆阻滞力
Figure 16. Linkage blocking force for the 100th and 500th cycles
表 1 各级叶片角度一致性
Table 1. Consistency of blade angle at each stage
$m $ $ \bar \sigma_{m} $/（°） $ f_{m} $/（°） 0 2.276 2.134 1 1.945 0.981 2 1.064 0.988 3 1.085 0.712 4 1.054 0.343 
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