CN112287552A - Aero-engine vibration trend analysis method - Google Patents

Aero-engine vibration trend analysis method Download PDF

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CN112287552A
CN112287552A CN202011191369.7A CN202011191369A CN112287552A CN 112287552 A CN112287552 A CN 112287552A CN 202011191369 A CN202011191369 A CN 202011191369A CN 112287552 A CN112287552 A CN 112287552A
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vibration
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fundamental frequency
frequency
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CN112287552B (en
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赵建平
毛宁
牛伟
王国振
喻鸣
于正同
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Xian Aeronautics Computing Technique Research Institute of AVIC
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Abstract

The invention belongs to the technical field of engine state monitoring, and provides an analysis method for vibration trend of an aero-engine, which is mainly used for monitoring vibration states of components such as a low-pressure rotor, a high-pressure rotor and an accessory casing of the engine. The method solves the problems of large data volume and low analysis reliability and accuracy of the existing method for analyzing the performance state trend of the rotating part of the engine, and comprises the following steps: the method comprises the steps of obtaining fundamental frequency and frequency multiplication amplitude information of a rotor system by using a time domain synchronous averaging method, using rotating speed stability, vibration amplitude stability and rotating speed error as quality factors for judging the steady state of a rotating part of the engine, and using vibration data as the basis of steady state trend analysis only when the quality factors of the rotating part meet set steady state conditions, so that reliable and accurate trend prediction can be realized under the same external environment as much as possible, and when the performance of the engine is degraded, properly reduced quality factors can be selected as steady state judgment conditions, so that the trend analysis flexibility is improved.

Description

Aero-engine vibration trend analysis method
Technical Field
The invention belongs to the technical field of engine state monitoring, and is mainly used for monitoring the vibration states of components such as a low-pressure rotor, a high-pressure rotor and an accessory casing of an engine. The airborne method for analyzing the vibration trend of the engine rotating system judges the vibration state of the transmission system and provides vibration information for an engine monitoring system.
Background
The vibration signal is one of important signals reflecting the working state of the engine, and the vibration signal contains a large amount of running state information of the system. At present, vibration signal processing is an effective method for diagnosing faults of an aircraft engine, and most faults in structural strength are closely related to vibration signals. Therefore, engine vibration monitoring is an important part of condition monitoring and fault diagnosis. Through relevant sensor, can gather the various vibration signals of engine, through the real-time detection to vibration signal's amplitude, vibration intensity, phase place isoparametric, combine the intrinsic characteristic of vibration signal, but the running condition of real-time supervision engine avoids the accident to take place and causes the loss for the enterprise. Therefore, the frequency spectrum information of the vibration signal has important significance for the dynamic characteristic and the fault characteristic of the engine, and the research on the vibration signal frequency measuring method has very important engineering significance.
The engine is an important part working in severe environment, high working strength and other environments, so that the engine is prone to failure, the state change rule is difficult to master, and the performance is difficult to predict accurately, so that trend analysis of the performance state of the rotating part of the engine is always an insurmountable technical bottleneck for improving the safe operation of aviation weaponry, accurate trend analysis of the performance state of the rotating part of the engine is realized, the performance change condition of the rotating part of the engine is mastered constantly, the failure of the rotating part of the engine is predicted as soon as possible, and the method is one of important means for ensuring flight safety and improving attendance rate. However, most of the existing methods for analyzing the performance of the rotating parts of the engine cannot obtain accurate and reliable trend analysis results, and have the defects of inaccurate analysis results and large errors. Chinese patent CN106599823A, "a performance trend prediction method for helicopter transmission gears", describes a performance trend analysis method for helicopter transmission gears, which applies a time domain analysis method to perform feature extraction on collected vibration signals of helicopter transmission gears, applies an entropy weight method to fuse feature values, and finally applies a gray theory algorithm to construct a gray prediction model, so as to realize reliable and accurate trend prediction for the performance state of helicopter transmission gears. However, the patent needs to use all vibration data for trend analysis, and the reliability and accuracy of the trend analysis may be affected by the large amount of calculation. For example, the external air flow at a certain time affects the vibration condition, and the data at this time is not suitable for trend analysis.
Disclosure of Invention
In order to solve the problems of large data volume and low analysis reliability and accuracy of the existing engine rotating part performance state trend analysis method, the invention provides the high-reliability and high-accuracy aircraft engine vibration trend analysis method, so that the prediction capability of the aircraft engine vibration state trend is improved.
In order to achieve the purpose, the technical scheme of the invention is as follows:
the method for analyzing the vibration trend of the aircraft engine is characterized by comprising the following steps of:
step 1, obtaining vibration and rotation data of a rotating part of an engine;
1.1, selecting vibration data and rotating speed of an engine rotating component N whole rotating periods, wherein N is an integer greater than 1;
1.2, calculating vibration fundamental frequency or frequency multiplication amplitude data of the engine by using a time domain synchronous averaging method; the engine fundamental frequency is the rotating speed frequency of an engine rotating component;
step 2, setting a quality factor;
using the sum of the rotating speed stability, the vibration fundamental frequency amplitude stability and the rotating speed error as a quality factor for judging the steady state of the rotating part of the engine;
step 3, screening vibration data suitable for vibration trend analysis according to the quality factor;
step 3.1, dividing the whole flight segment into a plurality of time segments, wherein each time segment is Dt, and Dt is greater than at least 2 times of N whole rotation periods;
step 3.2, obtaining vibration fundamental frequency or frequency multiplication amplitude data of the rotating part of the engine in each time period Dt;
3.3, calculating corresponding quality factors by using the vibration fundamental frequency or frequency multiplication amplitude data and the rotating speed data in each time period Dt;
step 3.4, comparing the quality factors corresponding to all time periods, and selecting vibration fundamental frequency or frequency multiplication amplitude data in the time period with the minimum quality factor as vibration data for vibration trend analysis; the smaller the quality factor is, the more stable the state of the rotating component is, and generally, a time period with the minimum quality factor is selected as vibration data for steady-state trend analysis in each target rotating speed of a flight segment;
step 4, drawing a curve according to the screening data, and predicting the vibration trend of the rotating part of the engine;
and (3) for the whole flight segment, drawing a time-varying curve of the steady-state fundamental frequency or the frequency doubling amplitude of the engine by using the vibration fundamental frequency or the frequency doubling amplitude data screened in the step (3), and predicting the vibration trend of the rotating component of the engine by using the time-varying curve of the fundamental frequency or the frequency doubling amplitude. The vibration fundamental frequency or the frequency multiplication amplitude is increased, and the performance of the engine is deteriorated.
Further, in step 2:
the rotating speed stability refers to the fluctuation condition of the rotating speed signal in a set time period
Figure BDA0002752847540000031
Wherein dN isWave motiondN is the difference between the maximum and minimum values of the rotational speed in a set period of timeThreshold (THD)Setting a rotation speed fluctuation threshold;
the stability of the vibration fundamental frequency amplitude refers to the fluctuation of the vibration fundamental frequency amplitude in a set time period
Figure BDA0002752847540000032
Wherein | dVWave motionL is the difference between the maximum value and the minimum value of the vibration fundamental frequency or the frequency doubling amplitude in a set time period, dVThreshold (THD)The vibration fundamental frequency or the frequency multiplication amplitude fluctuation threshold is set;
the rotation speed error is a rotation speed signal in a set time period
Figure BDA0002752847540000033
And a set rotation speed NExpectation ofDifference of (2)
Figure BDA0002752847540000034
Wherein dN isError thresholdIs a rotational speed error threshold;
Figure BDA0002752847540000035
the average value of the rotating speed in a set time period is obtained;
the quality factor is:
Figure BDA0002752847540000036
wherein alpha, beta and delta are proportionality coefficients.
The invention also provides another method for analyzing the vibration trend of the aircraft engine, which is characterized by comprising the following steps of:
step 1, obtaining vibration and rotation data of a rotating part of an engine;
1.1, selecting vibration data and rotating speed of an engine rotating component N whole rotating periods, wherein N is an integer greater than 1;
1.2, calculating vibration fundamental frequency or frequency multiplication amplitude data of the engine by using a time domain synchronous averaging method, wherein the engine fundamental frequency is the rotating speed frequency of an engine rotor;
step 2, setting a threshold;
setting a speed fluctuation threshold dNThreshold (THD)Vibration fundamental frequency amplitude fluctuation threshold dVThreshold (THD)And a rotational speed error threshold dNThreshold (THD)(ii) a According to the selection and setting of the engine performance, when the engine performance is better, the threshold value can be properly reduced, when the engine performance is poorer, the threshold value is properly enlarged, and the threshold value is an optional set and generally does not exceed 3 sets;
step 3, preliminarily screening vibration data suitable for vibration trend analysis according to a threshold;
step 3.1, dividing the whole flight segment into a plurality of time segments, wherein each time segment is Dt, and Dt is greater than at least 2 times of N whole rotation periods;
step 3.2, obtaining vibration fundamental frequency or frequency multiplication amplitude data of the rotating part of the engine in each time period Dt;
step 3.3, calculating the stability of the rotating speed, the stability of the amplitude of the vibration fundamental frequency and the error of the rotating speed by using the vibration fundamental frequency or frequency multiplication amplitude data and the rotating speed data in each time period Dt, and selecting the vibration data and the rotating speed data in the time period Dt with the stability of the rotating speed, the stability of the amplitude of the vibration fundamental frequency and the error of the rotating speed all less than 1 as the preliminary screening data in the step 4;
the rotational speed stability is:
Figure BDA0002752847540000041
wherein dN isWave motiondN is the difference between the maximum and minimum values of the rotational speed in a set period of timeThreshold (THD)Setting a rotation speed fluctuation threshold;
the stability of the amplitude of the vibration fundamental frequency is as follows:
Figure BDA0002752847540000042
wherein | dVWave motionL is the difference between the maximum value and the minimum value of the vibration fundamental frequency or the frequency doubling amplitude in a set time period, dVThreshold (THD)The vibration fundamental frequency or the frequency multiplication amplitude fluctuation threshold is set;
the error of the rotating speed is as follows:
Figure BDA0002752847540000043
wherein dN isError thresholdIs a threshold for the error in the rotational speed,
Figure BDA0002752847540000044
to set the average value of the rotational speed in the time period, NExpectation ofThe set time period is Dt, wherein the set time period is a rotating speed expected value;
step 4, screening again vibration data suitable for vibration trend analysis according to the quality factor;
4.1, respectively calculating the quality factors of the primarily screened vibration data and rotation speed data in each time period Dt;
the quality factor is:
Figure BDA0002752847540000045
wherein alpha, beta and delta are proportionality coefficients;
step 4.2, comparing the quality factors of the vibration data and the rotating speed data in all the time periods Dt primarily screened out, and selecting the vibration fundamental frequency or frequency multiplication amplitude data in the time period with the minimum quality factor as vibration data for vibration trend analysis;
step 5, drawing a curve according to the screening data, and predicting the vibration trend of the rotating part of the engine;
and (4) for the whole flight range, drawing a time-varying curve of the steady-state fundamental frequency or the frequency doubling amplitude of the engine by using the vibration fundamental frequency or the frequency doubling amplitude screened in the step (4), and predicting the vibration trend of the rotating component of the engine by using the time-varying curve of the fundamental frequency or the frequency doubling amplitude. The vibration fundamental frequency or the frequency multiplication amplitude is increased, and the performance of the engine is deteriorated.
The invention has the beneficial effects that:
1. the method uses the rotating speed stability, the vibration fundamental frequency amplitude stability and the rotating speed error as quality factors for judging the steady state of the rotating part of the engine, and only when the quality factors of the rotating part meet the set steady state conditions, the vibration data in the time period can be used as the basis of steady state trend analysis, so that reliable and accurate trend prediction can be realized under the same external environment as much as possible; by means of trend prediction of performance states of rotating parts, the operating state is mastered as early as possible, early diagnosis and prediction are achieved, and safe operation of the rotating parts of the engine is improved.
2. The invention uses a time domain synchronous averaging method to obtain the vibration fundamental frequency and frequency multiplication amplitude information of the rotating component system, and can effectively filter noise and inhibit interference signals.
3. The invention selects a proper fluctuation threshold to carry out preliminary screening aiming at the data of the rapid rotation, and then, the stability judgment condition is taken as the quality factor, thereby improving the flexibility of trend analysis.
4. When the performance of the engine is degraded, a properly reduced quality factor can be selected as a steady state judgment condition, and the flexibility of trend analysis is improved.
Detailed Description
The invention is further described below with reference to specific examples.
Example one
The method for analyzing the vibration trend of the aircraft engine comprises the following steps:
step 1, obtaining vibration and rotation data of a rotating part of an engine;
1.1, selecting vibration data and rotating speed of an engine rotating component N whole rotating periods, wherein N is an integer greater than 1;
1.2, calculating vibration fundamental frequency or frequency multiplication amplitude data of the engine by using a time domain synchronous averaging method; the engine fundamental frequency is the rotating speed frequency of an engine rotating component;
step 2, setting a quality factor;
using the sum of the rotating speed stability, the vibration fundamental frequency amplitude stability and the rotating speed error as a quality factor for judging the steady state of the rotating part of the engine;
the rotating speed stability refers to the fluctuation condition of the rotating speed signal in a set time period
Figure BDA0002752847540000061
Wherein dN isWave motiondN is the difference between the maximum and minimum values of the rotational speed in a set period of timeThreshold (THD)Setting a rotation speed fluctuation threshold;
the stability of the vibration fundamental frequency amplitude refers to the fluctuation of the vibration fundamental frequency amplitude in a set time period
Figure BDA0002752847540000062
Wherein | dVWave motionL is the difference between the maximum value and the minimum value of the vibration fundamental frequency or the frequency doubling amplitude in a set time period, dVThreshold (THD)The vibration fundamental frequency or the frequency multiplication amplitude fluctuation threshold is set;
the rotation speed error is a rotation speed signal in a set time period
Figure BDA0002752847540000063
And a set rotation speed NExpectation ofDifference of (2)
Figure BDA0002752847540000064
Wherein dN isError thresholdIs a rotational speed error threshold;
Figure BDA0002752847540000065
the average value of the rotating speed in a set time period is obtained; the set time in this embodiment is 10 seconds.
The quality factor is:
Figure BDA0002752847540000066
wherein alpha, beta and delta are proportionality coefficients.
Step 3, screening vibration data suitable for vibration trend analysis according to the quality factor;
step 3.1, dividing the whole flight segment into a plurality of time segments, wherein each time segment is Dt, and Dt is greater than at least 2 times of N whole rotation periods;
step 3.2, obtaining vibration fundamental frequency or frequency multiplication amplitude data of the rotating part of the engine in each time period Dt;
3.3, calculating corresponding quality factors by using the vibration fundamental frequency or frequency multiplication amplitude data and the rotating speed data in each time period Dt;
step 3.4, comparing the quality factors corresponding to all time periods, and selecting vibration fundamental frequency or frequency multiplication amplitude data in the time period with the minimum quality factor as vibration data for vibration trend analysis; the smaller the quality factor is, the more stable the state of the rotating component is, and generally, a time period with the minimum quality factor is selected as vibration data for steady-state trend analysis in each target rotating speed of a flight segment;
step 4, drawing a curve according to the screening data, and predicting the vibration trend of the rotating part of the engine;
and (3) for the whole flight segment, drawing a time-varying curve of the steady-state fundamental frequency or the frequency doubling amplitude of the engine by using the vibration fundamental frequency or the frequency doubling amplitude data screened in the step (3), and predicting the vibration trend of the rotating component of the engine by using the time-varying curve of the fundamental frequency or the frequency doubling amplitude. The vibration fundamental frequency or the frequency multiplication amplitude is increased, and the performance of the engine is deteriorated.
Such as: the engine desired speed is known as NExpectation of100Hz, the vibration sampling frequency is Fs 25KHz, the period calculation time is 200ms, the number of vibration data points corresponding to one rotation of the engine rotor is equal to Fs/NExpectation ofSelecting vibration data of 15 whole rotor rotation periods to perform time domain synchronous average calculation, wherein the vibration data is 250;
rotational speed fluctuation threshold dNThreshold (THD)2Hz, vibration fundamental frequency amplitude fluctuation threshold dVThreshold (THD)5mm/s, speed error threshold dNError thresholdThe proportionality coefficients α, β, and δ are all 1 at 1 Hz.
Within 10 seconds, the actual average engine speed N1AVG is 100.5Hz, and the speed fluctuates | dNWave motion1Hz, calculating the vibration fundamental frequency amplitude by using time domain synchronous average every 200ms, and the vibration fundamental frequency amplitude fluctuates by dV within 10 secondsWave motion2mm/S, error in rotation speed
Figure BDA0002752847540000071
So that the rotational speed is stable
Figure BDA0002752847540000072
Error in rotational speed
Figure BDA0002752847540000073
Stability of amplitude of vibration fundamental frequency
Figure BDA0002752847540000074
The figure of merit is then 1.15 in 10 seconds. And continuously comparing the quality factors in one flight, and finally selecting a vibration fundamental frequency amplitude corresponding to the minimum quality factor as a trend analysis characteristic value of the flight.
Analyzing characteristic values (namely vibration fundamental frequency amplitude) of the vibration trend of a plurality of flight ranges, drawing a curve of the change of the steady-state fundamental frequency vibration amplitude of the engine along with time, and realizing the prediction of the performance deterioration trend of the rotating part of the engine, wherein the vibration fundamental frequency amplitude is increased and the vibration performance of the engine is deteriorated.
Example two
The method for analyzing the vibration trend of the aircraft engine comprises the following steps:
step 1, obtaining vibration and rotation data of a rotating part of an engine;
1.1, selecting vibration data and rotating speed of an engine rotating component N whole rotating periods, wherein N is an integer greater than 1;
1.2, calculating vibration fundamental frequency or frequency multiplication amplitude data of the engine by using a time domain synchronous averaging method, wherein the engine fundamental frequency is the rotating speed frequency of an engine rotor;
step 2, setting a threshold;
setting a speed fluctuation threshold dNThreshold (THD)Vibration fundamental frequency amplitude fluctuation threshold dVThreshold (THD)And a rotational speed error threshold dNThreshold (THD)(ii) a According to the selection and setting of the engine performance, when the engine performance is better, the threshold value can be properly reduced, when the engine performance is poorer, the threshold value is properly enlarged, and the threshold value is an optional set and generally does not exceed 3 sets;
step 3, preliminarily screening vibration data suitable for vibration trend analysis according to a threshold;
step 3.1, dividing the whole flight segment into a plurality of time segments, wherein each time segment is Dt, and Dt is greater than at least 2 times of N whole rotation periods;
step 3.2, obtaining vibration fundamental frequency or frequency multiplication amplitude data of the rotating part of the engine in each time period Dt;
step 3.3, calculating the stability of the rotating speed, the stability of the amplitude of the vibration fundamental frequency and the error of the rotating speed by using the vibration fundamental frequency or frequency multiplication amplitude data and the rotating speed data in each time period Dt, and selecting the vibration data and the rotating speed data in the time period Dt with the stability of the rotating speed, the stability of the amplitude of the vibration fundamental frequency and the error of the rotating speed all less than 1 as the preliminary screening data in the step 4;
the rotational speed stability is:
Figure BDA0002752847540000081
wherein dN isWave motiondN is the difference between the maximum and minimum values of the rotational speed in a set period of timeThreshold (THD)Setting a rotation speed fluctuation threshold;
the stability of the amplitude of the vibration fundamental frequency is as follows:
Figure BDA0002752847540000082
wherein | dVWave motionL is the difference between the maximum value and the minimum value of the vibration fundamental frequency or the frequency doubling amplitude in a set time period, dVThreshold (THD)The vibration fundamental frequency or the frequency multiplication amplitude fluctuation threshold is set;
the error of the rotating speed is as follows:
Figure BDA0002752847540000083
wherein dN isError thresholdIs a threshold for the error in the rotational speed,
Figure BDA0002752847540000084
to set the average value of the rotational speed in the time period, NExpectation ofThe set time period is Dt, wherein the set time period is a rotating speed expected value;
step 4, screening again vibration data suitable for vibration trend analysis according to the quality factor;
4.1, respectively calculating the quality factors of the primarily screened vibration data and rotation speed data in each time period Dt;
the quality factor is:
Figure BDA0002752847540000091
wherein alpha, beta and delta are proportionality coefficients;
step 4.2, comparing the quality factors of the vibration data and the rotating speed data in all the time periods Dt primarily screened out, and selecting the vibration fundamental frequency or frequency multiplication amplitude data in the time period with the minimum quality factor as vibration data for vibration trend analysis;
step 5, drawing a curve according to the screening data, and predicting the vibration trend of the rotating part of the engine;
and (4) for the whole flight range, drawing a time-varying curve of the steady-state fundamental frequency or the frequency doubling amplitude of the engine by using the vibration fundamental frequency or the frequency doubling amplitude screened in the step (4), and predicting the vibration trend of the rotating component of the engine by using the time-varying curve of the fundamental frequency or the frequency doubling amplitude. The vibration fundamental frequency or the frequency multiplication amplitude is increased, and the performance of the engine is deteriorated.

Claims (3)

1. An aircraft engine vibration trend analysis method is characterized by comprising the following steps:
step 1, obtaining vibration and rotation data of a rotating part of an engine;
1.1, selecting vibration data and rotating speed of an engine rotating component N whole rotating periods, wherein N is an integer greater than 1;
1.2, calculating vibration fundamental frequency or frequency multiplication amplitude data of the engine by using a time domain synchronous averaging method; the engine fundamental frequency is the rotating speed frequency of an engine rotating component;
step 2, setting a quality factor;
using the sum of the rotating speed stability, the vibration fundamental frequency amplitude stability and the rotating speed error as a quality factor for judging the steady state of the rotating part of the engine;
step 3, screening vibration data suitable for vibration trend analysis according to the quality factor;
step 3.1, dividing the whole flight segment into a plurality of time segments, wherein each time segment is Dt, and Dt is greater than at least 2 times of N whole rotation periods;
step 3.2, obtaining vibration fundamental frequency or frequency multiplication amplitude data of the rotating part of the engine in each time period Dt;
3.3, calculating corresponding quality factors by using the vibration fundamental frequency or frequency multiplication amplitude data and the rotating speed data in each time period Dt;
step 3.4, comparing the quality factors corresponding to all time periods, and selecting vibration fundamental frequency or frequency multiplication amplitude data in the time period with the minimum quality factor as vibration data for vibration trend analysis;
step 4, drawing a curve according to the screening data, and predicting the vibration trend of the rotating part of the engine;
and (3) for the whole flight segment, drawing a time-varying curve of the steady-state fundamental frequency or the frequency doubling amplitude of the engine by using the vibration fundamental frequency or the frequency doubling amplitude data screened in the step (3), and predicting the vibration trend of the rotating component of the engine by using the time-varying curve of the fundamental frequency or the frequency doubling amplitude.
2. The aircraft engine vibration trend analysis method of claim 1, wherein in step 2:
the rotating speed stability refers to the fluctuation condition of the rotating speed signal in a set time period
Figure FDA0002752847530000011
Wherein dN isWave motiondN is the difference between the maximum and minimum values of the rotational speed in a set period of timeThreshold (THD)Setting a rotation speed fluctuation threshold;
the stability of the vibration fundamental frequency amplitude refers to the fluctuation of the vibration fundamental frequency amplitude in a set time period
Figure FDA0002752847530000021
Wherein | dVWave motionL is the difference between the maximum value and the minimum value of the vibration fundamental frequency or the frequency doubling amplitude in a set time period, dVThreshold (THD)The vibration fundamental frequency or the frequency multiplication amplitude fluctuation threshold is set;
the rotation speed error is a rotation speed signal in a set time period
Figure FDA0002752847530000022
And a set rotation speed NExpectation ofDifference of (2)
Figure FDA0002752847530000023
Wherein dN isError thresholdIs a rotational speed error threshold;
Figure FDA0002752847530000024
the average value of the rotating speed in a set time period is obtained;
the quality factor is:
Figure FDA0002752847530000025
wherein alpha, beta and delta are proportionality coefficients.
3. An aircraft engine vibration trend analysis method is characterized by comprising the following steps:
step 1, obtaining vibration and rotation data of a rotating part of an engine;
1.1, selecting vibration data and rotating speed of an engine rotating component N whole rotating periods, wherein N is an integer greater than 1;
1.2, calculating vibration fundamental frequency or frequency multiplication amplitude data of the engine by using a time domain synchronous averaging method, wherein the engine fundamental frequency is the rotating speed frequency of an engine rotor;
step 2, setting a threshold;
setting a speed fluctuation threshold dNThreshold (THD)Vibration fundamental frequency amplitude fluctuation threshold dVThreshold (THD)And a rotational speed error threshold dNThreshold (THD)；
Step 3, preliminarily screening vibration data suitable for vibration trend analysis according to a threshold;
step 3.1, dividing the whole flight segment into a plurality of time segments, wherein each time segment is Dt, and Dt is greater than at least 2 times of N whole rotation periods;
step 3.2, obtaining vibration fundamental frequency or frequency multiplication amplitude data of the rotating part of the engine in each time period Dt;
step 3.3, calculating the stability of the rotating speed, the stability of the amplitude of the vibration fundamental frequency and the error of the rotating speed by using the vibration fundamental frequency or frequency multiplication amplitude data and the rotating speed data in each time period Dt, and selecting the vibration data and the rotating speed data in the time period Dt with the stability of the rotating speed, the stability of the amplitude of the vibration fundamental frequency and the error of the rotating speed all less than 1 as the preliminary screening data in the step 4;
the rotational speed stability is:
Figure FDA0002752847530000031
wherein dN isWave motiondN is the difference between the maximum and minimum values of the rotational speed in a set period of timeThreshold (THD)Setting a rotation speed fluctuation threshold;
the stability of the amplitude of the vibration fundamental frequency is as follows:
Figure FDA0002752847530000032
wherein | dVWave motion| is a vibration base in a set time periodDifference between maximum and minimum of frequency or frequency-doubled amplitude, dVThreshold (THD)The vibration fundamental frequency or the frequency multiplication amplitude fluctuation threshold is set;
the error of the rotating speed is as follows:
Figure FDA0002752847530000033
wherein dN isError thresholdIs a threshold for the error in the rotational speed,
Figure FDA0002752847530000034
to set the average value of the rotational speed in the time period, NExpectation ofThe set time period is Dt, wherein the set time period is a rotating speed expected value;
step 4, screening again vibration data suitable for vibration trend analysis according to the quality factor;
4.1, respectively calculating the quality factors of the primarily screened vibration data and rotation speed data in each time period Dt;
the quality factor is:
Figure FDA0002752847530000035
wherein alpha, beta and delta are proportionality coefficients;
step 4.2, comparing the quality factors of the vibration data and the rotating speed data in all the time periods Dt primarily screened out, and selecting the vibration fundamental frequency or frequency multiplication amplitude data in the time period with the minimum quality factor as vibration data for vibration trend analysis;
step 5, drawing a curve according to the screening data, and predicting the vibration trend of the rotating part of the engine;
and (4) for the whole flight range, drawing a time-varying curve of the steady-state fundamental frequency or the frequency doubling amplitude of the engine by using the vibration fundamental frequency or the frequency doubling amplitude screened in the step (4), and predicting the vibration trend of the rotating component of the engine by using the time-varying curve of the fundamental frequency or the frequency doubling amplitude.
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CN114323664A (en) * 2021-12-13 2022-04-12 中国船舶重工集团公司第七0三研究所 Method for detecting abnormal gas vibration of gas turbine
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