Aero-engine rotor blade end timing signal time frequency rearrangement method

Through the combination of the finite element model and the normal distribution probability density function, the difficulty of monitoring the vibration parameters of the aircraft engine blade in high noise environment is solved, and the time-frequency representation aggregation and continuity of the blade-end timing signal is improved, which is more accurate time-frequency analysis.

CN119122629AActive Publication Date: 2024-12-13XI AN JIAOTONG UNIV +1
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Patent Information

Application Number
CN202411021545.0
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-07-29
Publication Date
2024-12-13
Estimated Expiration
2044-07-29

AI Technical Summary

Technical Problem

The vibration parameters of the aircraft engine blades are difficult to accurately monitor in high noise environments, resulting in insufficient time-frequency aggregation and continuity of sparse time-frequency reconstruction results.

Method used

The blade modal frequency is calculated by finite element model, the prior frequency in the Campbell graph is obtained, combined with the sparse time-frequency reconstruction method, the measured frequency is extracted, the normal distribution probability density function is constructed, the posterior frequency is generated, and the time-frequency point is The amplitude magnitude redistributes the weights to improve the aggregation and continuity of time-frequency representations.

Benefits of technology

The time-frequency representation aggregation and continuity of the leaf-end timing signal is significantly improved, the influence of noise interference is reduced, and a more accurate time spectrum diagram is obtained.

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Abstract

The invention relates to an aero-engine rotor blade end timing signal time frequency rearrangement method, which comprises the following steps of: acquiring blade dynamic frequencies under different rotating speeds from a Campbell diagram of a rotor blade of an aero-engine rotor as prior frequencies; obtaining the time-frequency representation of rotor blade vibration from the under-sampled blade end timing signal by using a blade end timing sparse time-frequency reconstruction method, and extracting the frequency with the maximum amplitude from the time-frequency representation as the actually measured frequency; estimating the dynamic frequency of the rotor blade based on the prior frequency and the actually measured frequency to obtain a posterior frequency; and determining the weight of each time-frequency point according to the size of the time-frequency coefficient, and redistributing the time-frequency coefficient to the vicinity of the posterior frequency according to the weight of each time-frequency point.
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Citation Information

Patent Citations

  • Blade inherent frequency identification method based on multiple blade tip timing sensors

    CN113404555A

  • An aero-engine blade damage online identification method

    CN113987871A

  • Blade inherent frequency identification method based on minimum variance power spectrum estimation

    CN115636105A

Cited By

  • Method and system for reconstructing timing undersampling vibration signal of rotating blade of aero-engine

    CN120145091A