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针对航空发动机叶片-机匣碰摩故障,提出了一种新型叶片-机匣碰摩模型,该模型在传统弹性碰摩模型的基础上,考虑了叶片数和转静间隙变化对碰摩力的影响,能够模拟机匣单点、多点、局部及全周,转子的单点、多点、局部和全周的碰摩规律.将所提出的碰摩模型运用于转子-支承-机匣耦合动力学模型中,利用数值积分获取碰摩故障下的机匣加速度响应规律.利用带机匣的航空发动机转子实验器,进行了叶片-机匣的机匣单点-转子全周的碰摩实验,发现了机匣振动加速度信号的碰摩特征具有明显的周期冲击特征,其冲击频率为叶片通过机匣的频率,在数值上等于旋转频率与叶片数的乘积,在频谱高频段出现了叶片通过频率及其倍频,冲击的大小受旋转频率调制,倒频谱具有旋转频率及其倍频的倒频率成分,仿真和实验取得了很好的一致性,验证了所提出的叶片-机匣碰摩新模型的正确有效性.最后,在此基础上,仿真计算了多种碰摩模式下的机匣振动特征和规律.
In order to solve the problem of aero-engine blade-hub rubbing, a new blade-hub rubbing model is proposed. Based on the traditional elastic rub-impact model, Can simulate single point, multi-point, partial and whole-week, single-point, multi-point, partial and whole-week rubbing laws of the casing.The proposed rubbing model is applied to the rotor-bearing- In the dynamic model, the response of the casing’s acceleration under rub-impact fault was obtained by using the numerical integral method. The rotor-stator of the aero-engine with casing was used to conduct a single point rotor-rotor test It is found that the rubbing characteristic of the vibration signal of the receiver has obvious periodic impact characteristics. The impact frequency is the frequency of the blade passing through the receiver, and is numerically equal to the product of the rotating frequency and the number of blades. Frequency and its frequency multiplication, the size of the impact is modulated by the rotation frequency, the cepstrum has the rotation frequency and the overtone frequency of the frequency multiplication, the simulation and the experiment have achieved very good consistency, and verified the proposed blade- Correct validity of the model. Finally, based on this, the vibration characteristic simulation casing under various laws and Rub mode.