CAJ | 학술논문

研究了航空压气机呼吸裂纹叶片在转子位移激励下的联合共振幅频响应的变化规律；叶片连续体模型采用伽辽金法简化成单自由度的系统模型，通过多尺度法导出了叶片在参数激励与位移激励联合作用下的共振幅频响应的一阶近似方程；分析了裂纹的开合深度、裂纹所在截面的位置以及转子在垂直与水平方向上的位移幅值差对幅频响应的影响；数值结果表明以上三个物理参数是促使叶片动力学行为发生变化的敏感参数，控制这三个物理参数的变化是有效防止叶片进一步破坏的根本途径。
연구료항공압기궤호흡렬문협편재전자위이격려하적연합공진폭빈향응적변화규률；협편련속체모형채용가료금법간화성단자유도적계통모형，통과다척도법도출료협편재삼수격려여위이격려연합작용하적공진폭빈향응적일계근사방정；분석료렬문적개합심도、렬문소재절면적위치이급전자재수직여수평방향상적위이폭치차대폭빈향응적영향；수치결과표명이상삼개물리삼수시촉사협편동역학행위발생변화적민감삼수，공제저삼개물리삼수적변화시유효방지협편진일보파배적근본도경。
The amplitude-frequency response of combination resonance of an aero-engine compressor blade with a breathing crack under the lateral displacement excitation of the rotor shaft was investigated.The blade was simplified into a single degree of freedom system using Galerkin’s method.The first order equation of the resonance response under parametric excitation combining with displacement excitation was derived by using the multi-scale method.The effects of the opening and closing depth of crack,the location of lateral section with crack and the displacement amplitude of rotor shaft on the amplitude-frequency response of resonance were analyzed.The obtained results show that controlling the changes of the above mentioned parameters which are of great influence on the dynamic behavior is an effective measure for preventing fatigue of the blade.