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航空发动机特殊的鼓式压气机结构可简化为径向转动惯量大于轴向转动惯量的厚盘转子系统,其做正进动时存在两个固有频率.计算了单-厚盘转子分别以定角加速度和定功率过两阶临界转速时对不平衡激振力的瞬态响应,其中定功率厚盘转子还与外界能源发生非线性耦合.结果发现,单-厚盘转子的低阶振型为轴的弯曲,高阶振型为盘的偏摆,其中高阶模态是厚盘转子特有模态;过临界转速时瞬态振动由转子的自由振动和强迫振动合成;当功率不足够提供转子通过临界转速时,出现外界能源与转子系统的能量耦合,造成瞬态振动急剧增大而“失速”.
Aeroengine’s special drum compressor structure can be simplified as a thick disk rotor system with radial moment of inertia larger than axial moment of inertia and two natural frequencies at forward and forward motions.A single- The transient responses of unbalanced exciting force to acceleration and constant power over two critical speeds are obtained, in which the constant-power thick disc rotor is also non-linearly coupled with the external energy source. The results show that the low- When the critical speed is exceeded, the transient vibration is synthesized by the free vibration and forced vibration of the rotor. When the power is not enough to provide the rotor to pass the critical speed , The energy coupling between the external energy source and the rotor system appears, causing the transient vibration to increase sharply and “stall”.