Surge Warning and Identification Method of Aero-engine Based on Blade Vibration

doi:10.3901/JME.2024.21.122

Abstract

Abstract: Surge is a typical fault of engine, which is extremely harmful, especially under the state of acceleration, so timely diagnosis and early warning is especially critical. The traditional early warning method of surge is based on pressure pulsation signals, which are difficult to install and has a limited identification range of the sensors. The blade tip timing technology is widely concerned in the condition monitoring of turbomachinery. The traditional blade asynchronous identification algorithm does not adequately analyze the under-sampling problem, and the identification accuracy is greatly affected by the frequency aliasing. So through the change of the frequency and amplitude characteristics of the blades, a method is proposed for surge warning and blade frequency identification. The lumped parameter model of blades considering detuning and coupling is established, the frequency difference is corrected by the combination of APFFT and traditional FFT, the natural number are obtained by the apfft and the traversal algorithms. The accuracy of natural number is introduced and the obviousness of frequency difference is proposed as a criterion to obtain an accurate asynchronous recognition algorithm. A numerical simulation model is used to simulate the displacement under-sampling data of the blade collected by the BTT sensor during multi-frequency resonance, and comparing the identification results of the two algorithms, the maximum error of the proposed modified algorithm is 0.845% and 0.053% for the difference and frequency identification, respectively, which is much lower than that of the traditional algorithm, which is 1.556% and 0.097%, and the accuracy of the proposed algorithm is verified. Experiments are carried out on the large fan blade test bench, the frequency amplitude characteristics of blade in the stage of surge are investigated, real-time warning of surge is realized according to the amplitude effective value and alarm threshold, and the proposed algorithm is used to identify the blade asynchronous vibration frequency. The experimental results show that the setting of the blade amplitude alarm threshold during surge is in good agreement with the displacement results, and the average of asynchronous vibration frequency is 1 261.2 Hz, and the maximum deviation is 4.8%. This method can provide real-time non-contact surge warning for turbomachinery, and provide technical support for asynchronous frequency identification and damage monitoring of turbine rotating blades.

Key words: blade tip timing, surge warning, asynchronous vibration, frequency identification

CLC Number:

TK14
V211

WANG Weimin, LIU Yanzhen, LIN Yulong, LI Tianqing. Surge Warning and Identification Method of Aero-engine Based on Blade Vibration[J]. Journal of Mechanical Engineering, 2024, 60(21): 122-131.

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