Method for extracting fault signal feature information of aero-engine rotor system

Abstract

The invention discloses a method for extracting the fault signal feature information of an aero-engine rotor system, and the method comprises the steps: collecting a rotor rub-impact vibration signal,and carrying out the FDM decomposition of the collected rotor rub-impact vibration signal to obtain complete rotor rub-impact vibration signal FIBFs components; constructing a Hankel matrix of the rotor rub-impact vibration signal after noise reduction, and drawing a singular value curve of the rotor rub-impact vibration signal after noise reduction; determining a singular value catastrophe point, carrying out the reconstruction of an order number, and carrying out the envelope spectrum analysis, thereby achieving the effective extraction of fault information. According to the invention, themethod achieves the reasonable extraction of the fault feature frequency of a rotor system based on the FDM decomposition and singular value differential spectrum analysis, and achieves the efficientfiltering of the noise signal component in the rub-impact vibration signal, thereby achieving the extraction of the weak fault feature information from the low-frequency strong noise background, and achieving the effective extraction of the fault information.

Description

technical field

[0001] The invention relates to a method for extracting feature information of signals, in particular to a method for extracting feature information of fault signals of an aeroengine rotor system. Background technique

[0002] The aircraft engine is the heart of the aircraft. It is the system with the highest failure rate, the most complicated adjustment and the largest maintenance workload in the aviation machinery equipment. The quality of its working status directly affects the safety, reliability and operation of the aircraft. Once the engine fails during operation, it may cause the aircraft to fail to fly normally, endanger personal safety, and cause significant social and economic losses.

[0003] According to statistics, the failure rate of aero-engines accounts for about 30% of all aircraft failures, and about 40% of major flight accidents due to mechanical reasons are caused by engine failures. Engines are different from general machinery due to thei...

Examples

Embodiment example

[0072] An implementation case of the method for extracting characteristic information of the fault signal of the aeroengine rotor system, including the following process:

[0073] The first step is to collect the rubbing vibration signal of the aero-engine rotor; through the eddy current displacement sensor, select 1000 sets of rubbing vibration signal data samples of the aero-engine rotor at a speed of 2000r / min, and set the sampling frequency of the signal to 1000Hz;

[0074] by formula Construct FM and AM timing simulation signal x 1 (t), simulated signal x 1 (t) contains a non-linear frequency modulation signal x 11 (t) and a frequency-modulated amplitude-modulated signal x with a certain period 12 (t), the sampling frequency of the set signal is 1000Hz;

[0075] signal x 1 The time-domain waveform of (t) is as follows figure 1 shown. Among them, the signal x 1 The waveform diagram of (t) presents complex waveform pulse characteristics without significant periodic...

technical field

[0001] The invention relates to a method for extracting feature information of signals, in particular to a method for extracting feature information of fault signals of an aeroengine rotor system. Background technique

[0002] The aircraft engine is the heart of the aircraft. It is the system with the highest failure rate, the most complicated adjustment and the largest maintenance workload in the aviation machinery equipment. The quality of its working status directly affects the safety, reliability and operation of the aircraft. Once the engine fails during operation, it may cause the aircraft to fail to fly normally, endanger personal safety, and cause significant social and economic losses.

[0003] According to statistics, the failure rate of aero-engines accounts for about 30% of all aircraft failures, and about 40% of major flight accidents due to mechanical reasons are caused by engine failures. Engines are different from general machinery due to thei...

Examples

Embodiment example

[0072] An implementation case of the method for extracting characteristic information of the fault signal of the aeroengine rotor system, including the following process:

[0073] The first step is to collect the rubbing vibration signal of the aero-engine rotor; through the eddy current displacement sensor, select 1000 sets of rubbing vibration signal data samples of the aero-engine rotor at a speed of 2000r / min, and set the sampling frequency of the signal to 1000Hz;

[0074] by formula Construct FM and AM timing simulation signal x 1 (t), simulated signal x 1 (t) contains a non-linear frequency modulation signal x 11 (t) and a frequency-modulated amplitude-modulated signal x with a certain period 12 (t), the sampling frequency of the set signal is 1000Hz;

[0075] signal x 1 The time-domain waveform of (t) is as follows figure 1 shown. Among them, the signal x 1 The waveform diagram of (t) presents complex waveform pulse characteristics without significant periodic...

Images