CAJ | 학술논문

利用航空发动机转子试验器模拟不同部位的碰摩，测试获得碰摩时机匣的加速度响应信号，并与无碰摩时机匣加速度时、频域波形进行对比。测试结果表明，航空发动机叶盘结构的转子—机匣碰摩时，其加速度信号具有冲击、调幅特征，即在碰摩频率及其整数倍频附近存在边频带，其边频宽度为旋转频率。同时，与无碰摩状态相比，在低频段时碰摩特征主要表现为转频及其倍频分量，且倍频分量更加突出。
이용항공발동궤전자시험기모의불동부위적팽마，측시획득팽마시궤갑적가속도향응신호，병여무팽마시궤갑가속도시、빈역파형진행대비。측시결과표명，항공발동궤협반결구적전자—궤갑팽마시，기가속도신호구유충격、조폭특정，즉재팽마빈솔급기정수배빈부근존재변빈대，기변빈관도위선전빈솔。동시，여무팽마상태상비，재저빈단시팽마특정주요표현위전빈급기배빈분량，차배빈분량경가돌출。
Using the aeroengine’s rotor-stator testing rig, the rub-impact performance of the rotor-stator system was simulated, and the acceleration signals and the wave forms in frequency domain of the rotor-stator case under rub-impact status were obtained and compared with those without rub-impact phenomenon. The results show that when the rub-impact happens, the acceleration signals have impact and amplitude modulation characteristics, i.e. there exist some sidebands in the vicinity of rubbing frequency and the n-th harmonic frequencies (where n is an integer). In the low frequency range, the rubbing was characterized by the rotation frequency and the n-th harmonic components, and usually these components were more obvious than the former.