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为了评估航空发动机应变片粘贴误差对振动应力测量结果的影响程度,利用有限元计算与蒙特卡洛分析方法对压气机转子叶片的贴片方案进行了研究,并提出基于可靠度的贴片方案优化准则。分析结果表明:当贴片位置由应变梯度较小的B点移动至应变梯度较大的A点时,相对应变误差增加了0.5倍,贴片可靠度降低了0.3倍;当贴片方向与最大主应变方向之间的夹角由0°增加至30°时,相对应变误差增大了0.6倍,贴片可靠度降低了0.4倍;根据可靠度准则,所选贴片方案可同时对两阶模态的振动应力进行有效测量,其可靠度达到限制值0.9以上,表明将该准则用于贴片方案寻优是合适的。
In order to evaluate the effect of the aero-engine strain gauge pasting error on the vibration stress measurement results, a finite element method and a Monte Carlo analysis method are used to study the placement scheme of the compressor rotor blade, and the optimization of the patch scheme based on the reliability Guidelines. The results show that when the position of the patch moves from point B where the strain gradient is smaller to point A where the strain gradient is larger, the relative strain error increases by 0.5 times and the reliability of the patch by 0.3 times. When the patch orientation is the maximum When the angle between the main strain directions increases from 0 ° to 30 °, the relative strain error increases by 0.6 times, and the reliability of the patch decreases by 0.4 times. According to the reliability criterion, the selected patch scheme can be applied to two orders Modal vibration stress effective measurement, the reliability of the limit value of 0.9 or more, indicating that the criteria for the patch scheme optimization is appropriate.