针对航空发动机整机振动特征溯源困难的现状，以某型发动机典型振动突变特征溯源研究为例，提出了一种基于整机及部件动力学试验手段的振动特征溯源研究方法。该方法首先通过整机及部件动力学试验测试手段揭示发动机动力学特性和典型现象深层特征，然后通过综合剖析方法溯源振动特征的动力学原因及结构原因。通过发动机全静子机匣支承动刚度和整机模态特性试验研究，获取了静子支承动刚度特性与整机模态特性。通过发动机转子全转速下动特性与转子模态试验研究，揭示了转子在离心载荷作用下的不平衡激励和弹性线变化规律，以及转子连接界面在不同力学参数下的模态特性。通过整机工作条件下的转子轴承座全息测振和基于发动机叶尖间隙的转子全息测振试验研究，揭示了发动机典型振动特征的瞬变特征、支点工作振型、转子涡动及初相点等特征的变化规律。经综合研判，得到了该发动机振动突变特征的原因是转子连接界面变化所引发的转子不平衡激励状态突变的结论。基于该机理开展了转子本机平衡技术研究，有效地抑制了多台发动机的振动突变特征，进一步表明该溯源方法的正确性。

To address the difficulty in feature traceability of whole aeroengine vibration， this paper proposes a research method for vibration feature traceability based on dynamic experiments of whole aeroengines and parts， with the study of typical vibration mutation feature traceability of an aeroengine as an example. This method firstly reveals the dynamic properties of the engine and deep features of typical phenomena by dynamic experiments of the whole aeroengine and parts， and then traces to the dynamic and structural causes of vibration features through comprehensive analysis. Properties of supporting dynamic stiffness of the stator and modal characteristics of the whole aeroengine are obtained by experimental study on supporting dynamic stiffness of the whole stator casing and modal characteristics of the whole aeroengine. The experimental study on the dynamic properties and modality of full speed rotors reveals the imbalance excitation and elastic line changing rule of rotors with centrifugal load， and the modal properties of the rotor joint interface with different mechanical parameters. Holographic vibration measurement of the rotor bearing block under working conditions of the whole aeroengine and that of the rotor based on the blade tip interval of the engine show the changing rule of the transient characteristics of the classical vibration feature， support point vibration modal， vortex motion of the rotor and primary phase spots. As found from comprehensive study and judgment， the vibration mutation characteristic of the aeroengine results from the rotor imbalance excitation status mutation caused by the change in the joint interface of the rotor. The study on the rotor balance technique based on this mechanism is conducted and the result shows that the vibration mutation properties of multiple aeroengines are effectively suppressed， further proving the correctness of this tracing method.