A novel method of weakness imbalance fault identification and application in aerohydraulic pump
Mingyue Yu^{1} , Jincai Cheng^{2} , Hui Pan^{3} , Runze Zhang^{4} , Zeli Lin^{5}
^{1, 2, 3, 4}Shenyang Aerospace University, Shenyang, China
^{5}AeroMeasurement and Control Technology Research, Shanghai, China
^{1}Corresponding author
Journal of Vibroengineering, Vol. 21, Issue 1, 2019, p. 5265.
https://doi.org/10.21595/jve.2018.19858
Received 2 April 2018; received in revised form 30 August 2018; accepted 7 September 2018; published 15 February 2019
JVE Conferences
A method of combining autocorrelation and Hilbert envelope analysis is proposed and used to identify weakness imbalance fault of aerohydraulic pump, the central part of hydraulic system of aircraft. Firstly, the integral and polynomial least square fitting is applied to convert acceleration signal to velocity one; secondly, the Hilbert envelope spectrum of autocorrelation function of velocity signal is obtained and used to identify the weakness imbalance fault of aerohydraulic pump; finally, the energy ratio of velocity signal is calculated according to Hilbert envelope spectrum for identifying imbalance fault of aerohydraulic pump by means of easier and more visual method. Meanwhile, the comparing analysis is carried out between traditional research method and proposed new one. The result shows that the weakness imbalance fault of aerohydraulic pump can be identified and diagnosed effectively and correctly according to the velocity signal whether Hilbert envelope spectrum or calculation energy ratio while direct acceleration signal cannot.
Keywords: energy ratio, casing vibration signal, aerohydraulic pump, autocorrelation function, velocity signal.
1. Introduction
Imbalance is a kind of representative fault in largescale rotation machine, like aeroengine, and according to statistics, 60 % of equipment faults were caused by mass unbalance [1, 2]. Aerohydraulic pump is the central part of hydraulic system of aircraft. Statistics show that the hydraulic system faults accounts for 40 percent of all total aircraft faults, and 15 to 20 percent of faults are aroused directly by hydraulic system fault [3]. The power input shaft fault of aerohydraulic pump is a typical fault, which results in insufficient pressure or excessive volatility, and failure of actuators which take hydraulic source as power to achieve its expected function. For example, undercarriage cannot fold or release in time; wheel brake system cannot response in time, and so on. Based on the above considerations, in the coupler of aviation hydraulic pump close to power input shaft, weakness imbalance fault is set by mounting an imbalance bolt.
Due to the limitation of hydraulic pump structure, casing is usually the only device to monitor its running states [4]. Based on the wavelet packet decomposition and wavelet coefficients residual analysis method, the fault diagnosis approach employing the outlet pressure of pump is proposed for improving the accuracy of fault diagnosis of hydraulic pump by Gao, et al., in 2009 [5]. In 2012, Tang, et al., combined envelope spectrum analysis and empirical mode decomposition (EMD) to identify the early faults of pump based on vibration signal [6]. The casing signal is a comprehensive reflection of many parts [7, 8]. The signal distortion, energy attenuation and noise effect drastically increases the weakness and complexity of fault characteristics information of casing signal [9], and tremendously increases the difficulty of fault diagnosis in largescale rotation machines.
Velocity is an ideal parameter to reflect vibration for most equipment, and its virtual value is a measurement standard of vibration faults identification across the globe [10]. But velocity sensor has a large size and can only be installed in fixed position through the specific installing seat in state monitoring, which limits the application of velocity sensor to some extent [11]. Acceleration sensor is smaller in size with lighter weight [11], and can be conveniently installed in different positions. While acceleration signal is more sensitive to highfrequency signal [11], it works in such a way that the higher frequency, the greater enlargement effect will be. Considering that common aeroengine realtime monitoring frequency is not high, and the vibration standard for identification faults of rotor system is usually according to velocity or displacement signal [10] rather than acceleration signal, some methods which can change acceleration signal to velocity or displacement signal are proposed [1214]. Generally, integral method is used to transform the acceleration signal to velocity signal in practice, where the conversion will produce certain errors and trend terms [12]. Method of least square by using polynomials can eliminate baseline shift of liner conditions and high order polynomial trend terms, which is the most common method to eliminate trend terms in engineering practice [12, 13]. Integral method is combined with least square by polynomial in order to convert acceleration signal to velocity and displacement signal and to identify the rotorstator rubbing position of aeroengine; meanwhile, the displacement signal obtained by converting acceleration signal and collecting directly is compared and verified in terms of the similarity and consistence from timedomain and frequencydomain, for example [14]. In consideration of the aerohydraulic pump structure, the cyclic impact will be generated on the status of fault occurrence. Therefore, the faults characteristics can be extracted by demodulation modulatedvibration signal through envelope spectrum analysis. Hilbert transform can obtain the complex envelope of signal with regular vibration components removed and signal modulated information remained without the load frequency composition [15]. Signal autocorrelation function can reserve the periodic component and eliminate noise at the same time, and meanwhile can change frequency modulation to amplitude modulation [16]. Based on above considerations, a method of combining integral, polynomial least square fitting, with autocorrelation and Hilbert envelope analysis is proposed. Meanwhile energy ratio among frequency multiplication of rotation frequency and total low frequency bands is calculated and used to identify weakness imbalance fault of aerohydraulic pump according to casing velocity signal in proposed new method.
2. Theoretical basis
2.1. Hilbert transform [17]
The formulas for the basic discrete Hilbert transform (DHT) of discrete data $x\left(n\right)$, where $n=(\mathrm{\infty},\cdots ,\mathrm{1,0},1,\cdots ,\mathrm{\infty})$ are as follows:
The inverse discrete Hilbert transform is given as:
The transformation for the DHT matrix $H$, input vector $F$, and the output vector $G$ can be written as $G=HF$.
Then obtain the amplitude function of $x\left(n\right)$, namely the Hilbert envelope spectrum ${A}_{i}\left(n\right)$:
2.2. Autocorrelation function
A continuous signal $x\left(t\right)$ is defined, then ${R}_{x}(t,\tau )$, the autocorrelation function of continuous $x\left(t\right)$ such that:
Given $\tau $, $E\left\{\u2022\right\}$ and $*$ is respectively delay factor, statistical mean value and complex convolution.
2.3. The relationship of velocity and acceleration signal
Suppose a velocity signal $x\left(t\right)$ can be express as follows:
${A}_{i}$ represents vibration amplitude in different frequency; $N$ is period number of $x\left(t\right)$; $f$ represents the basic frequency of velocity signal; ${\phi}_{i}$ is initial phase angle, and then acceleration signal $y\left(t\right)$ can be expressed:
$N=\left\{\mathrm{1,2},3,\dots ,\right\},i=\left\{1,\dots ,N\right\}.$
Comparing the amplitude of Eq. (5) and (6), it can find that the acceleration signal $y\left(t\right)$ has amplitude amplification effect on velocity signal, and meanwhile the higher frequency $(i\times 2\pi f)$, the greater amplitude enlargement effect will be. That is why acceleration signal is more sensitive to high frequency signal than velocity signal.
2.4. Energy of velocity signal
The velocity signal is corresponding with the energy of signal. A vibration signal $x\left(n\right)$ and its Fourier transform $x\left(k\right)$ are defined, and then its energy $E\left({x}^{2}\right)$ of $x\left(k\right)$ such that:
$N$ represents the length of $x\left(k\right)$. Suppose a frequency band is given, then the energy of this frequency band can be calculated according to Eq. (7). Meanwhile, the energy ratio $P\left({x}^{2}\right)$ of different selected frequency bands can be shown as follows:
where ${m}_{1}$, ${m}_{2}$, ${n}_{1}$, ${n}_{2}$ respectively represents the staring and end points of different selected frequency bands of $x\left(k\right)$, and $P\left({x}^{2}\right)$ is the energy ratio of different selected frequency bands.
3. Weakness imbalance fault identification of aerohydraulic pump
In consideration of the aerohydraulic pump structure, the cyclic impact will be generated. Therefore, the faults characteristics can be extracted by demodulation modulatedvibration signal through envelope spectrum analysis. Signal’s autocorrelation function can reserve the periodic component and eliminate noise at the same time, which is excellently fit for cyclic signal of rotation machine. Based on above considerations, autocorrelation function and Hilbert envelope analysis is combined and used to diagnose imbalance fault of aerohydraulic pump. The specific scheme is shown in Fig. 1. Fig. 1(a) is the common traditional study method which combines acceleration signal and Hilbert envelope analysis to identify and diagnose imbalance fault of rotor system; Fig. 1(b) is the proposed new method which combines autocorrelation function and Hilbert envelope analysis for identifying and diagnose weakness imbalance fault of rotor system of rotation machine in this paper.
Fig. 1. Fault diagnosis method comparisons for: a) common traditional research method at present, b) proposed new method in this paper
a)
b)
Compared with Fig. 1(a) and Fig. 1(b), the difference is highlighted, and they are shown as follows:
1) The casing vibration acceleration signal is converted to velocity signal firstly, and all further analysis is based on convertobtained velocity signal in new method;
2) The autocorrelation function is used to reduce noise for velocity signal before Hilbert envelope analysis;
3) Not only the fault characteristics are extracted, but also the energy ratio is calculated and used to identify and diagnose weakness imbalance fault of aerohydraulic pump in proposed new method.
The concrete steps based on proposed new method are as follows:
1) The casing vibration acceleration signal is collected on the status of the transmission shaft weakness imbalance fault occurrence and normal running of aerohydraulic pump;
2) The vibration acceleration signal is converted to velocity signal by integral combining with polynomial least square fitting method.
3) The autocorrelation function of velocity signal is used to reduce the noise.
4) The Hilbert envelope spectrum of autocorrelation function of velocity signal is obtained and used to identify weakness imbalance faults of aerohydraulic pump.
5) Finally, the energy ratio is calculated according to Hilbert envelope spectrum of autocorrelation function of velocity signal. Meanwhile, the energy ratio is used to identify and diagnose weakness imbalance fault on the status of power input axis weak imbalance fault occurrence and normal running of aerohydraulic pump.
4. Aerohydraulic pump weak imbalance fault experiment
In this paper, all experiment data comes from some types of aerohydraulic pumps shown Fig. 2, which is designed by Aeroengine Corporation of China (AECC) HARBIN DONGAN Engine CO., LTD. The hydraulic pump is swashplate axial piston pump, and the numbers of plungers are nine. The coupler is used to connect hydraulic pump and driver motor because the shaft size cannot match between hydraulic pump and motor. The weakness imbalance fault is set in couple close to power input shaft of hydraulic pump by adding an imbalance bolt. The hydraulic pump and specific position of imbalance bolt is shown in Fig. 2. The size and weight of imbalance bolt is respectively M6*10 cm and 0.045 kg. The rotating speed measured by SE series eddy current displacement sensors which is provided by instrument factory Southeast University. Data collector Model is USB9234 provided by National Instruments. The acceleration sensor is installed on mounting seat of aerohydraulic pump, and the direction is vertical, which is shown in Fig. 2.
Fig. 2. Imbalance fault experiment of aerohydraulic pump
Experiment data of weakness imbalance fault is randomly selected, and the rotational speed is about 2500 r/min; all the 1T4T respectively represents 14 integer multiple rotating frequency; all scheme A is corresponding with the traditional analysis method at present as shown in Fig. 1(a); all scheme B is corresponding with proposed new method as shown in Fig. 1(b) which is marked by orange in this paper; all scheme C is corresponding with proposed new method as shown in Fig. 1(b) which is marked by orange and pink in this paper; (the scheme B and C is the same before Hilbert envelope spectrum. The difference is that the Hilbert envelope spectrum of autocorrelation function of velocity signal is directly used to identify fault in scheme B; while the energy ratio obtained by Hilbert envelope spectrum is calculated and used to identify fault in scheme C) the polynomialfitting orders 13 is selected by comparing according to the method that is proposed in the reference [14] involved in the paper.
5. Aerohydraulic pump weakness imbalance fault identification
5.1. Traditional studied: scheme A – Fig. 1(a)
We randomly take the weakness imbalance fault data collected by the accelerometer in vertical direction as an example for analysis. The rotating speed is 2469 r/min and the rotating frequency is 41.2 Hz by calculating (1469/60 = 41.2). The fuel feeding pulse frequency is equal to 370.8 Hz (nine times of rotation frequency as the number of plungers is nine). The Hilbert envelope spectrum of casing acceleration signal is obtained and the result is shown in Fig. 3, 4. The Fig. 3 is the time domain of acceleration signal. Fig. 4 is the Hilbert envelope spectrum and its local amplification corresponding with Fig. 3.
Fig. 3. Timedomain of acceleration signalimbalance fault occurrence
Fig. 4. Hilbert envelope spectrum and its local amplification for: a) Hilbert envelope spectrum, b) Hilbert envelope spectrum local amplificationimbalance fault occurrence: scheme A
a)
b)
Analyzing Fig. 4, the following conclusions can be draw:
1) In Fig. 4(a), the fuel feeding pulse frequency (374 Hz) and its frequency multiplication is highlighted, and meanwhile, the twice rotation frequency is also more significant.
2) The Fig. 4(b) is the Hilbert envelope spectrum local amplification of Fig. 4(a) in lowfrequency band. Analyzing Fig. 4(b), it can find that twice rotation frequency is more significant than rotation frequency itself, which is not matching with the imbalance fault set of aerohydraulic pump (the amplitude of rotation frequency is significantly increased and highlighted when imbalance fault occurs).
The misdiagnosis would probably be caused if acceleration signal is selected directly to identify and diagnose fault types of rotor system just like Fig. 4(a), (b). In Fig. 4(a), (b), the twice rotation frequency is more significant than rotation frequency itself, and the other fault types, such as misalignment, sliding boots loose instead of imbalance fault can probably be considered, and thereby leads to the misdiagnosis.
Analyzing the reason according to Eq. (5), (6), it can be found that comparing with velocity signal, the amplitude has been enlarged $(i\times 2\pi f)$ times in acceleration signal. The frequency is higher (the $(i\times 2\pi f)$ is larger), and the enlargement effect is more significant. Meanwhile the vibration identification standard for faults of rotor system is usually according to velocity or displacement signal [10] rather than acceleration signal.
5.2. Proposed new method: Scheme BFig. 1(b) (marked by orange)
Considering that vibration identification standard for faults of rotor system is usually based on velocity or displacement signal rather than acceleration signal [10]. The misdiagnosis would probably be caused if acceleration signal is selected directly to identify and diagnose fault types of rotor system just like Section 5.1. According to the above considerations, the velocity signal is obtained by combining integral with polynomial least square fitting method. For comparing, the same data as Section 5.1 is selected, and the result is shown in Fig. 5, 6. The Fig. 5 is the time domain of velocity signal. Fig. 6(a), (b) is respectively Hilbert envelope spectrum and its local amplification corresponding with Fig. 5. The velocity signal that obtained by using integral combining with polynomial least square fitting method and the polynomialfitting orders is 13.
Fig. 5. Timedomain of velocity signalimbalance fault occurrence
Fig. 6. Hilbert envelope spectrum and its local amplification of velocity signal imbalance fault occurrence for: a) Hilbert envelope spectrum, b) Hilbert envelope spectrum local amplification
a)
b)
After analyzing Fig. 6 and comparing with Fig. 4 (acceleration signal directly), the following conclusions can be drawn:
1) Hilbert envelope spectrum of velocity signal which is obtained according to acceleration signal, the component frequency is similar with acceleration signal to some degree (such as the same highlighted fuel feeding pulse frequency (374 Hz) and its frequency multiplication);
2) While the rotation frequency is more significant in Fig. 6 than Fig. 4. The amplitude enlargement effect of velocity signal has been decreased compared with acceleration signal.
However, the misdiagnosis would also probably be caused if velocity signal is analyzed just by Hilbert envelope analysis due to the influence of 23 times rotation frequency just like shown as Fig. 6.
For further correctly and effectively identifying weak imbalance fault of aerohydraulic pump based on casing vibration signal, the Hilbert envelope analysis is combined with autocorrelation analysis. In order to compare and analyze accurately, the same data is selected. The autocorrelation function includes acceleration signal and velocity signal is acquired. Meanwhile, the Hilbert envelope spectrum of autocorrelation function is acquired including acceleration signal and velocity signal. The result is shown in Figs. 7, 8. Fig. 7 and Fig. 8 is respectively autocorrelation function and its Hilbert envelope spectrum. Fig. 7(a)Fig. 8(a) is corresponding with acceleration signal, and Fig. 7(b)Fig. 8(b) is corresponding with velocity signal.
Analyzing Fig. 7, 8, the following conclusions can be drawn:
1) Compared with Fig. 46 (Hilbert envelope analysis only), in Fig. 8, no matter for casing vibration acceleration signal or velocity signal, the noise is significantly reduced in their autocorrelation function and Hilbert envelope spectrum. It is due to the denoised function of autocorrelation function for cyclic signal.
2) Meanwhile, in the Fig. 8(a) the Hilbert envelope spectrum of autocorrelation of acceleration signal, the twice rotation frequency is the most significant in low frequency band. It is consistent with Fig. 4(b), and it is not matching with the imbalance fault set of aerohydraulic pump. The misdiagnosis would also probably be caused if acceleration signal is selected to identify and diagnose fault types of aerohydraulic pump.
3) In Fig. 8(b), the velocity signal obtained by converting acceleration signal, only the rotation frequency is highlighted in low frequency band. It is exactly matching the imbalance fault set of aerohydraulic pump.
Fig. 7. Autocorrelation function for: a) corresponding with acceleration signal, b) corresponding with velocity signalimbalance fault occurrence
a)
b)
Fig. 8. Hilbert envelope spectrum of autocorrelation function for: a) corresponding with acceleration signal, b) corresponding with velocity signalimbalance fault occurrence: scheme B
a)
b)
To further analyze the reason, Fig. 8(a) is corresponding with acceleration signal which leads to the amplified frequency amplitude. Meanwhile the noise is reduced due to autocorrelation function, which leads to the result of Fig. 8(a). Fig. 8(b) is corresponding with velocity signal, and the frequency multiplication enlargement effect is greatly decreased. Meanwhile the noise is reduced due to autocorrelation function, which leads to the result shown in Fig. 8(b). It can be found that the weakness imbalance fault of aerohydraulic pump cannot be identified and diagnosed when acceleration signal is directly selected. If acceleration signal is converted to velocity at first, and autocorrelation analysis is combined with Hilbert envelope analysis, the imbalance fault of aerohydraulic pump can be identified and diagnosed effectively.
5.3. The weakness imbalance fault identification according to calculation energy ratio: scheme C
For further identifying and diagnosing the weakness imbalance fault of aerohydraulic pump in easier and more visual method, the energy ratio of velocity is calculated. Meanwhile, in order to compare with velocity signal, the ratio of sum of mean square value in different selected frequency bands of acceleration signal is calculated. In view of the majority of faults of rotor system in rotation machine which certainly has manifestation on low order frequency multiplication of rotation frequency [10], the 14 frequency multiplication of rotate frequency is selected in this paper. The 1 to 4 are taken from subtracting 5 Hz to adding 5 Hz on the basis of calculation of rotation frequency, in the consideration that there is a deviation between theoretical calculation and practice obtaining. For example, suppose that rotation frequency is equal to $Q$ Hz by calculation, and then the rotation speed band is selected from ($Q$5) Hz to ($Q+$5) Hz, and double rotation frequency band is selected from (2$\times Q$5) Hz to (2$\times Q+$5) Hz and so on. Total lowfrequency band is selected from 0 Hz to 300 Hz in consideration that traditional aeroengine realtime monitoring frequency is not high and selected 14 times frequency is all contained (the 4T rotation frequency is equal to 4*41.2 = 164.8 Hz), and the result is shown in Fig. 9. Fig. 9(a) and Fig. 9(b) is respectively the ratio of sum of mean square value and energy ratio among different rotation frequency bands and total low frequency bands. Fig. 9(a) is corresponding with casing vibration acceleration signal, and meanwhile matching with scheme A. Fig. 9(b) is corresponding with velocity signal, and meanwhile matching with scheme C. The 1 to 4 of $x$axis respectively represents 14 multiplication rotation frequency.
Fig. 9. Ratio value of different scheme for: a) acceleration signalscheme A, b) velocity signalscheme C
a)
b)
By analyzing Fig. 9, it can find that the following conclusions:
1) The nature of result shown is consistent among figures. While Fig. 9(a), (b) is more visualized than Fig. 4(b) and Fig. 8(b), they are shown the ratio value among 1 to 4 integer multiplication rotational frequencies and total lowfrequency from 0 Hz to 300 Hz.
2) In Fig. 9(a) which is corresponding with acceleration signal and scheme A, the twice frequency of rotation speed is most highlighted than other multiplication frequencies, it is consistent with Fig. 4(b), which is also not matching with set imbalance fault of aerohydraulic pump. The other fault types, such as misalignment, sliding boots loose instead of imbalance fault can probably be considered, and thereby leads to the misdiagnosis.
3) In Fig. 9(b) which is corresponding with velocity signal, the rotation frequency is more highlighted than other integer multiplication frequencies, and it is exactly consistent with set imbalance fault of aerohydraulic pump.
The difference of calculation ratio value according to Hilbert envelope spectrum is highlighted between acceleration and velocity signal. The calculation of specific number of different multiplication frequencies according to acceleration signal and velocity signal is shown Table 1. All the 1T4T respectively represent 14 integer multiple rotating frequency; all scheme A corresponding with the traditional analysis method (scheme A). All scheme C corresponding with proposed new method combined with Hilbert envelope spectrum and autocorrelation analysis.
Analyzing further according to Table 1, it can find that the ratio value of rotation frequency is 0.057 that is corresponding with acceleration signal marked by blue based on scheme A. The ratio value of rotation frequency is small and not matching with set imbalance fault. Namely, it cannot identify and diagnose the weakness fault of aerohydraulic pump based on casing vibration acceleration signal according to Hilbert envelope analysis.
Table 1. Ratio value based on different analyze method
Signal types

Different scheme

Multiplication frequency of rotation speed


1T

2T

3T

4T


Acceleration signal

Scheme A

0.057

0.167

0.033

0.010

Velocity signal

Scheme C

0.221

0.042

0.019

0.008

However, the energy ratio of rotation frequency corresponding to velocity signal is 0.221 (marked in red basic on scheme C). The ratio value of rotation frequency is increased from 0.057 which is corresponding with acceleration signal and analyzed by scheme A to 0.221 which is corresponding with velocity signal and analyzed by proposed new method. The highlighted ratio value of rotation frequency is exactly matching with set weakness imbalance fault of aerohydraulic pump. That is, it was matched with set fault of aerohydraulic pump based on proposed new methods.
In order to verify the effectiveness and consistency of the proposed new method, the fifty groups data is randomly selected and respectively calculated and analyzed by traditional analysis method (scheme A) and proposed new method (scheme C). The result is shown in Table 2, 3 and Fig. 10. The Table 2 and Table 3 is the 10 groups ratio value which selected randomly from 50 groups date. Meanwhile, the Table 2 and Table 3 is respectively corresponding with traditional analysis method (scheme A) and proposed new method (scheme C). All the 1T4T respectively represent 14 integer multiple rotating frequency; Fig. 10 is the ratio value distribution diagram of selected 50 group date. Fig. 10(a) and Fig. 10(b) is respectively corresponding with traditional research method and proposed new method, and “∎”, “※”, “∆”, and “•” respectively represents the ratio value of 14 times rotation frequency band in Fig. 10.
Table 2. Ratio of sum of mean square value according to acceleration signal: scheme A
Frequency band

1T

2T

3T

4T

Sample number


1

0.078632

0.095693

0.025842

0.038186

2

0.080782

0.10016

0.036583

0.020041

3

0.066883

0.09981

0.027547

0.035887

4

0.081108

0.082662

0.032035

0.035165

5

0.070865

0.094358

0.030028

0.044432

6

0.081389

0.091382

0.031962

0.013943

7

0.070502

0.094347

0.037325

0.020138

8

0.075507

0.088422

0.033839

0.036911

9

0.081727

0.088363

0.038981

0.023991

10

0.069481

0.088715

0.02914

0.040883

Mean value of 50 samples

0.074472

0.099508

0.03232

0.027364

From Table 2, 3 and Fig. 10, the following conclusions can be drawn:
1) The consistency of calculation ratio value of each method is excellent whether acceleration signal is analyzed by scheme A or velocity signal is analyzed by scheme C (Hilbert envelope analysis combined with autocorrelation analysis).
2) Meanwhile, the consistency of Fig. 10(b) which is corresponding with velocity signal and proposed new method is more excellent than Fig. 10(a) which is corresponding with acceleration signal and traditional research method (scheme A).
3) In Table 2 and Fig. 10(a), the specific mean value of 50 samples of acceleration signal is about 0.074, 0.10, 0.032 and 0.027 for 14 times rotation frequency. The ratio of sum of mean square value of double rotation frequency band is the largest, which does not match set imbalance fault, and misdiagnosis could probably be caused.
4) In Table 3 and Fig. 10(b), the specific mean energy ratio of 50 samples of velocity signal is about 0.228, 0.038, 0.015 and 0.006 for 14 times rotation frequency. The energy ratio of rotation frequency band is more obvious and the largest, and it is exactly consistent with imbalance fault set of aerohydraulic pump.
Table 3. Energy ratio according to velocity signal: scheme C
Frequency band

1T

2T

3T

4T

Sample number


1

0.20407

0.044677

0.022163

0.0116

2

0.23573

0.035718

0.012898

0.003976

3

0.23925

0.03387

0.011664

0.003157

4

0.20642

0.044516

0.021852

0.011287

5

0.23703

0.03504

0.012276

0.003658

6

0.23486

0.036336

0.013553

0.004316

7

0.23497

0.036534

0.013507

0.004343

8

0.23763

0.034494

0.012074

0.00344

9

0.20448

0.044548

0.02218

0.011527

10

0.23653

0.035777

0.013116

0.003943

Mean value of 50 samples

0.228341

0.037912

0.015253

0.005866

Fig. 10. Ratio value based on different sample for: a) corresponding with acceleration signal: scheme A, b) corresponding with velocity signal: scheme C
a)
b)
5.4. Status monitor and identification on the status of aerohydraulic pump normal running: proposed new method
In normal running state of aerohydraulic pump, we convert acceleration signal to velocity signal by the same method of Section 5.15.3 where integral is combined with polynomial least square fitting method and the polynomialfitting order is also 13. The energy ratio is calculated based on proposed method according to obtained velocity signal. The rotation speed is 2346.2 r/min and the rotation frequency is equal to 39.1 Hz by calculation (2378.3/60 = 39.1). The result is shown in Fig. 11 and Table 4. The Fig. 11(a) is the transformed velocity, and the Fig. 11(b) is the autocorrelation function of velocity, and Fig. 11(c) is the Hilbert envelope spectrum of autocorrelation function of velocity signal, and Fig. 11(d) is the calculation energy ratio based on proposed scheme C. The Table 4 is the specific value of calculation energy ratio.
Analyzing the Fig. 11 and Table 4, and meanwhile comparing with weakness imbalance fault occurrence of aerohydraulic pump, the following conclusions can be drawn:
The energy ratio of rotation frequency is equal to 0.113 on the normal running status of aerohydraulic pump. While the ratio value is about equal to 0.228 (the mean value of energy ratio of 50 group samples shown is Table 3) on the weakness imbalance fault occurrence, which exceeds the twice of normal running condition. In the similar running environment, the energy ratio is also approximate, and therefore the sharp increased energy ratio can be used to identify weakness imbalance fault occurrence.
Fig. 12. Scheme Cnormal running of aerohydraulic pump for: a) velocity signal, b) autocorrelation function of velocity signal, c) Hilbert envelope spectrum of autocorrelation function of velocity signal, d) energy ratio based on scheme C
a)
b)
c)
d)
Table 4. Energy ratio based on proposed method (scheme C) on the condition of normal running of aerohydraulic pump
Signal types

Scheme

Frequency multiplication of rotation speed


1T

2T

3T

4T


Velocity signal

Scheme C

0.113

0.022

0.017

0.023

6. Conclusions
A method of combining autocorrelation function with Hilbert envelope analysis is proposed and used to identify weakness imbalance fault of aerohydraulic pump on the conditions of weakness imbalance fault occurrence and normal running. Meanwhile, the energy ratio can be calculated according to Hilbert envelope spectrum of autocorrelation function of velocity signal. The results show the following features:
1) The comparative analysis is implemented between Hilbert envelope analysis of acceleration signal and proposed new method of velocity signal. The result shows that either Hilbert envelope spectrum or calculation energy ratio corresponding with velocity signal can identify the weakness imbalance fault of aerohydraulic pump correctly and perfectly based on proposed new method.
2) While the acceleration signal cannot directly identify the weakness imbalance fault of aerohydraulic pump according to either Hilbert envelope spectrum or calculation energy ratios due to the amplitude enlargement effect of acceleration signal itself to frequency multiplication. It will lead to missing diagnosis or misdiagnosis if acceleration signal is directly used to identify and diagnose fault types of aerohydraulic pump.
3) The excellent consistency of proposed new method is verified by 50 groups of difference fault samples.
4) Finally, the comparative analysis is carried out between normal running and the operation with weakness imbalance fault occurrence of aerohydraulic pump based on proposed methods. The result shows that the energy ratio calculated based on proposed new method can effectively identify and diagnose if the weakness imbalance fault occurs in aerohydraulic pump.
The method should require further study in terms of the following aspects:
The proposed research method in this paper should be inspected in the actual project. The proposed method was inspected just by data of the aerohydraulic pump. As the real aeroengine structure is far more complex than experiment rig, and there are many types of external noises and vibrations in real flight, actual project inspection is required to determine the efficiency of extracting casing characteristics.
Acknowledgements
This work was supported by National Natural Science Foundation of China (Grant No. 51605309), Aeronautical Science Foundation of China (Grant No. 20163354004) and Provincial Education Department of Liaoning Province of China (Grant No. L201628).
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