When there is a difference in the rigidity of a rotor support, the vibration vector is affected by the mounting angle of the sensor, resulting in a difference in the dynamic balancing effect. By separating the time-domain data collected by two sensors in the direction orthogonal to the measurement point, the forward and backward precession components of the rotor vibration signal can be separated based on the Hilbert transform, and the amplitude and phase of the forward component can be extracted by using the cross-correlation method, so as to realize the measurement of the rotor imbalance vector. Based on this method, different rotors have been analyzed and the results verified by numerical simulation and experimental analysis. The simulation results show that the residual vibration at the bearing support position within the balanced speed range with our new method using multi-plane and multi-speed dynamic balancing is lower than that obtained after balancing with a single-direction sensor. The experimental results for a flexible rotor indicate that after using our new method for dynamic balancing, the residual vibration at critical speed is lower than that after using a single direction sensor for dynamic balancing. The results of the rigid rotor experiment show that after using this method for dynamic balancing and removing the influence of slow rolling vector, the vibration amplitude of the test rotor measurement point mainly due to imbalance decreases by at least 54.17%, while the corresponding measurement point amplitudes at single X and single Y direction measurement points decrease by 37.50% and 33.33%, respectively, after dynamic balancing. In summary, the proposed method can improve the accuracy of dynamic balancing and should have valuable engineering applications.

Blade tip timing technology has improved in recent years and is now frequently utilized in the monitoring and diagnosis of turbomachinery blade vibration. It is necessary to decouple the measurement results of blade tip timing and determine the axial displacement of the blade, because the measurement results of the blade tip-timing method are the components of the blade tip displacement in the rotational direction, and the change in the position of the measurement points for blade tip timing caused by the axial displacement of the blade also introduces the displacement components in the rotational direction. A blade axial displacement identification method based on the principle of blade tip timing measurement is proposed after analyzing the link between the change in measurement point position and the measurement result. Integrating the blade profile equation, a sample model of blade tip timing that incorporates blade axial displacement is established, and the efficiency of the proposed method is verified by simulation. The measured blade tip timing signals from the adjustable axial displacement aero-engine compressor blade are then used for experimental verification, and the axial displacement identification values of the rotor blade are compared with the actual values, verifying the accuracy of the proposed method. It has significant engineering application value for thoroughly and accurately assessing blade operation status and diagnosing rotor-blade axial displacement faults.