CN110134110A - Rotor crack fault detection method based on range restraint strategy - Google Patents
Rotor crack fault detection method based on range restraint strategy Download PDFInfo
- Publication number
- CN110134110A CN110134110A CN201910403658.XA CN201910403658A CN110134110A CN 110134110 A CN110134110 A CN 110134110A CN 201910403658 A CN201910403658 A CN 201910403658A CN 110134110 A CN110134110 A CN 110134110A
- Authority
- CN
- China
- Prior art keywords
- rotor
- rotor system
- axis
- crack
- interval
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001514 detection method Methods 0.000 title claims abstract description 24
- 230000004044 response Effects 0.000 claims abstract description 59
- 230000005284 excitation Effects 0.000 claims abstract description 39
- 238000000034 method Methods 0.000 claims description 24
- 238000011217 control strategy Methods 0.000 claims description 20
- 230000005484 gravity Effects 0.000 claims description 17
- 230000008569 process Effects 0.000 claims description 8
- 238000013016 damping Methods 0.000 claims description 4
- 230000001133 acceleration Effects 0.000 claims description 2
- 230000009466 transformation Effects 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000006243 chemical reaction Methods 0.000 abstract 1
- 230000009471 action Effects 0.000 description 6
- 238000004422 calculation algorithm Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 6
- 239000011159 matrix material Substances 0.000 description 5
- 230000003321 amplification Effects 0.000 description 4
- 238000003199 nucleic acid amplification method Methods 0.000 description 4
- 238000011160 research Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 230000000739 chaotic effect Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000003889 chemical engineering Methods 0.000 description 1
- 238000005094 computer simulation Methods 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 230000000875 corresponding effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005312 nonlinear dynamic Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- IUKLSMSEHKDIIP-UHFFFAOYSA-N petine Natural products CC1(O)C2CCC3C4CC(O)C5CC(O)CCC5(C)C4CC3C2CN2C1CCC(C)C2 IUKLSMSEHKDIIP-UHFFFAOYSA-N 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000001308 synthesis method Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
- G05B23/0221—Preprocessing measurements, e.g. data collection rate adjustment; Standardization of measurements; Time series or signal analysis, e.g. frequency analysis or wavelets; Trustworthiness of measurements; Indexes therefor; Measurements using easily measured parameters to estimate parameters difficult to measure; Virtual sensor creation; De-noising; Sensor fusion; Unconventional preprocessing inherently present in specific fault detection methods like PCA-based methods
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24065—Real time diagnostics
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention provides the rotor crack fault detection method based on range restraint strategy, belongs to aero-engine technology field.The low-pressure section that the present invention chooses aero-engine dual-rotor structure first establishes single spool system model, and establishes coordinate system；Then aircraft engine rotor system critical speed is calculated, and the target control section of revolving speed is set according to critical speed；Apply constant excitation in the Y direction at place to be detected, the target control section of revolving speed, establishes rotor dynamics model；It is vibratory response equation by the rotor dynamics model conversion；Amplitude-frequency response is drawn using vibratory response as the output signal of rotor-support-foundation system using parameters as the input signal of rotor-support-foundation system；Rotor crack fault is finally judged according to amplitude-frequency response.The present invention solves the problems, such as that the success rate of existing rotor crack fault detection is not high.The present invention can be used for aeroengine rotor crack detection.
Description
Technical Field
The invention relates to a rotor crack fault detection method, and belongs to the technical field of aircraft engines.
Background
With the development of society, the development of airplanes and aviation industry is more and more emphasized by countries all over the world. The aircraft engine, as a core for providing flight power, has a complex structure, is easily affected by factors such as excitation, temperature and the like, and has been a popular topic in the field of aviation. The cracks are an important failure mode of the engine rotor, and the research on the cracks has important significance in the aspects of production design, product detection and maintenance of the engine.
The existing crack models mainly comprise: the opening and closing of cracks and the change of the shaft rigidity of a square wave model (Hanjie, Zhang Ruelin. rotating machinery fault mechanism and diagnosis technology [ M ]. Beijing: mechanical industry Press, 1997) can be represented by a step function; the crack opening and closing state and the transition process and the crack depth are given by a cosine wave model (Schmied J. simulation behavior of a crack rotation a transient crack [ J ]. Journal of Mechanical Design,1980,102(1):140-146) roughly considering the transition process of the crack half-opening and half-closing, a comprehensive model (Gaojian, Zhuxiamei. research on the crack opening and closing model on the rotating shaft [ J ]. applied mechanics report, 1992,9(1)108-112), the relationship between the flexural states of the rotating shaft at the crack opening and closing site, a nonlinear model proposed by Men (Meng G, GaschR. the nonlinear equations of the periodic on the stability and stress of the angular rotor [ J ]. Journal of Machine Vibration,1992,4(2): 216) takes into account the relationship between the crack and the axial displacement, and a nonlinear crack opening and closing model considering the influence of the nonlinear vortex motion of the system is proposed.
The interval control strategy is quite common in practical engineering. The objective functions of interval predictive control and economic model predictive control are combined to obtain a novel control strategy which meets the control requirements and has better economic benefit, wherein the novel control strategy comprises the following steps of (1) Huminphenanthrene, permission 37574, Roxiong, interval predictive control with an economic cost function [ J ] chemical engineering progress, 2018,37(6) DOI:10.16085/j.issn.1000-6613.2017-1639) and the like; the Luo Xiong et al (Luo Xiong, Zhou Xiaolong, Zhu Limnu. Interval predictive control [ J ] control engineering, 2013,20(2):377-380.DOI:10.14107/j.cnki.kzgc.2013.03.037) provides an interval control algorithm based on a model predictive control theory, and Wanlanghao et al (Wanglanhao, Jiayao, Chatianyouyou. regrinding process pump pool liquid level and feeding pressure double-rate interval control [ J ] automated chemical report, 2017,43(6):993-1006.DOI:10.16383/j.aas.2017.c170134) eliminates a previous moment of non-dynamic compensation signals through design and superposes on a feedback controller designed based on a linear model, and provides a pump pool liquid level and feeding pressure double-rate interval control algorithm.
Under the natural condition without control, the crack rotor system has super harmonic resonance, but the response peak value is very small, the signal is very weak, and when the noise environment is considered, the crack fault characteristic signal is submerged in the noise signal and is difficult to effectively extract; the ultraharmonic resonance response amplitude may be amplified based on the principle that the applied constant excitation enables significant amplification of the ultraharmonic response characteristics of the cracked rotor system. Parametric excitations are common in engineering systems such as gravity effects in crack rotor systems and maneuvering loads of the rotor in maneuvering flight situations. There are many scholars in China who also have studied parameter incentives. Shaozi Wu et al (Shaozi Wu, Shaoshihua, Yang Tertiary. asymmetric rotor system parametric excitation forced vibration [ J ] vibration engineering report, 2002(03):71-74.DOI:10.16385/j.cnki.issn.1004-4523.2002.03.013) studied the forced vibration of the asymmetric rotor system under the action of parametric excitation, Yangdong et al (Yangdong, xu peimin, Shangpeng. split of the cracked rotor, chaotic behavior study [ J ] solid mechanics report, 2002(01):115-119.DOI:10.19636/j.cnki.cjsm42-1250/o3.2002.01.017) reported the nonlinear dynamic response of the cracked rotor system under the action of gravity, small cold charge (small cold charge, meng, zhao, Zhang, in the same way as the branched excitation of the cracked rotor system and the chaotic characteristic [ J ] vibration engineering report, 02) when random disturbance is considered, and the influence of the random rotor system on the random response of the cracked rotor system is considered, congratulating, et al (congratulating, Cheng cham. aeronautical reports, 2006(05): 835-. Therefore, the response characteristic of the rotor system under constant excitation can be used as the detection basis of the crack fault.
However, in the prior art, constant excitation is applied through a control algorithm, but constant excitation is applied in a super-harmonic resonance rotating speed region and outside the rotating speed region, so that not only is the main resonance of the system affected, but also the super-harmonic response characteristics of the amplified system are still difficult to identify, and the success rate of rotor crack fault detection is low.
Disclosure of Invention
The invention provides a rotor crack fault detection method based on an interval control strategy, aiming at solving the problem that the success rate of the existing rotor crack fault detection is not high.
The rotor crack fault detection method based on the interval control strategy is realized by the following technical scheme:
selecting a low-pressure part of a double-rotor structure of an aircraft engine to establish a single-rotor system model, and establishing a coordinate system; the coordinate system takes an end point of the coincidence of the rotor and the mass center of the aircraft as an origin o, the x axis of the coordinate system is parallel to the longitudinal axis of the fuselage of the aircraft and points to the advancing direction of the aircraft, the oy axis is positioned in the symmetrical plane of the aircraft, is vertical to the ox axis and points right above the aircraft, and the oz axis, the ox axis and the oy axis form a right-hand coordinate system;
calculating the critical rotating speed of the rotor system of the aircraft engine, and setting a target control interval of the rotating speed according to the critical rotating speed;
step three, applying constant excitation in a target control interval of the Y-axis direction and the rotating speed of the position to be detected, and establishing a rotor system dynamic model;
step four, converting the rotor system dynamic model into a vibration response equation;
fifthly, taking each parameter as an input signal of the rotor system, taking the vibration response as an output signal of the rotor system, and drawing an amplitude-frequency response curve;
and step six, judging the crack fault of the rotor according to the amplitude-frequency response curve in the step four.
The most prominent characteristics and remarkable beneficial effects of the invention are as follows:
the invention relates to a rotor crack fault detection method based on an interval control strategy, which takes a low-pressure compressor part of an aircraft engine rotor system as a research object, establishes a rotor system dynamic model, and realizes that constant excitation is applied in a super-harmonic resonance rotating speed region of a crack rotor system and a super-harmonic resonance response amplitude is amplified through a control algorithm, and excitation is not applied outside the rotating speed region, so that the influence on main resonance of the system is avoided. The constant excitation can generate obvious amplification effect on the super-harmonic resonance response of the crack rotor system, and the interval control strategy can obviously improve the success rate of crack fault detection of the rotor system; simulation experiments show that under the excitation of quintupling gravity constant, the amplitude of the super-harmonic response resonance peak is increased by 4.6 times by applying the method disclosed by the invention, and the effective detection of the crack fault of the subsystem under a noise environment can be realized.
Drawings
FIG. 1 is a schematic diagram of a single rotor system model established by the present invention;
FIG. 2 is a schematic view of a simulation process of a rotor system according to an embodiment of the present invention;
FIG. 3 is a graph of the amplitude-frequency response of the rotor system in an uncontrolled natural state in an embodiment; rad/s denotes radians per second;
FIG. 4 is a graph of the amplitude-frequency response of noise in the natural state without control in the embodiment;
FIG. 5 is a graph of magnitude-frequency response of the strategy in the noise-free environment in the embodiment;
FIG. 6 is a graph of the amplitude-frequency response of noise in the interval control strategy in the embodiment.
Detailed Description
The first embodiment is as follows: the present embodiment is described with reference to fig. 1, and the method for detecting a rotor crack fault based on a section control strategy according to the present embodiment specifically includes the following steps:
selecting a low-pressure part of a double-rotor structure of an aircraft engine to establish a single-rotor system model, and establishing a coordinate system; the coordinate system takes an end point of the coincidence of the rotor and the mass center of the aircraft as an origin o and is fixedly connected with the aircraft body, the rotor coordinate system is also an aircraft body coordinate system, the x axis of the coordinate system is parallel to the longitudinal axis of the aircraft body and points to the advancing direction of the aircraft, the oy axis is positioned in the symmetrical plane of the aircraft and is perpendicular to the ox axis and points right above the aircraft, and the oz axis, the ox axis and the oy axis form a right-hand coordinate system;
the double-rotor structure is the main structure form adopted by modern aeroengines, and the high-pressure rotor and the low-pressure rotor of the double-rotor structure are connected together through an intermediate bearing. Taking a certain type of aircraft engine as an example, a six-point supporting structure is adopted by a double-rotor system, wherein a high-pressure rotor system is of a two-pivot structure and adopts a supporting mode of 1-0-1; the low-pressure rotor system is of a four-pivot structure and adopts a 1-2-1 supporting mode. The method for reversible simplification of a dynamic model of an aeroengine rotor system [ J ] aerodynamics science report, 2016,31(1):57-64) establishes a relatively accurate complex dynamic discrete model, and the model establishes an 8-stage high-pressure compressor wheel disc, a 4-stage low-pressure compressor wheel disc and 1-stage high-low pressure turbine wheel discs. Research shows that the low-pressure compressor part of the double-rotor system is relatively independent and can be regarded as a single-rotor system. Therefore, a low-pressure part is selected to establish a single-rotor system model, as shown in figure 1;
calculating the critical rotating speed of the rotor system of the aircraft engine, and setting a target control interval of the rotating speed according to the critical rotating speed;
step three, applying constant excitation in a target control interval of the Y-axis direction and the rotating speed of the position to be detected, and establishing a rotor system dynamic model;
step four, converting the rotor system dynamic model into a vibration response equation;
fifthly, taking each relevant parameter as an input signal of the rotor system, taking the vibration response as an output signal of the rotor system, and drawing an amplitude-frequency response curve;
and step six, judging the crack fault of the rotor according to the amplitude-frequency response curve in the step four.
The second embodiment is as follows: the difference between this embodiment and the first embodiment is that the rotor system dynamics model in step three is specifically:
in the rotor system model shown in fig. 2, considering that a crack occurs at a packing and considering that constant excitation is applied in the y direction, a rotor system dynamic model as formula (1) is established, wherein m is the mass of the rotating disc, c is damping, c is 2 ξ m omega, ξ is a damping ratio, omega is rotating speed, △ k is crack stiffness and represents the influence of the crack depth on the rigidity of the rotating shaft, k is the supporting rigidity of the rotor system, y is the y-axis coordinate of the mass center of the rotating disc,first and second derivatives of y, respectively; t is time, and z is the z-axis coordinate of the center of mass of the turntable; e is the distance from the eccentric position of the turntable to the center of mass of the turntable, and g is the gravity acceleration; f. ofmIs an applied constant excitation.
Other steps and parameters are the same as those in the first embodiment.
The third concrete implementation mode: the difference between this embodiment and the second embodiment is that the specific process of converting the rotor system dynamic model into the vibration response equation in step four includes:
fourthly, carrying out dimensionless transformation on the rotor system dynamic model:
wherein, delta, s, tau, K, YZ is an intermediate variable; omeganIs the system natural frequency; f represents the influence of unbalanced excitation force, G represents the influence of gravity, H represents the influence of external constant excitation, and the numerical value represents the multiple of the external constant excitation relative to the gravity; in the rotor system model in the present invention, the constant excitation may be applied by an electromagnetic force. An electromagnetic field environment is built on the rotor system, and an overweight environment is simulated by utilizing the electromagnetic force, so that constant excitation occurs on the rotor system, and the effect of multiplying gravity is generated.
Then there are:
wherein,first and second derivatives of Y respectively,first and second derivatives of Z, respectively;
step four, solving the formula (1) by using a harmonic balance method:
let the solution of equation (3) be:
wherein A isi、Bi、Ci、DiIs the undetermined coefficient; i is 0,1, …, 4;
step four and three, the formula (4) is carried into the formula (3), the sum of the coefficients of each harmonic (the formula coefficients after the similar terms are combined by fingers) is made to be zero, and 18 coefficients related to A are obtainedi、Bi、Ci、DiSolving the algebraic equation to obtain 18 undetermined coefficients, and writing the undetermined coefficients into a matrix form, namely the vibration responseThe equation:
A＝R-1F′ (5)
wherein A ═ A1A2A3A4B1B2B3B4C0C1C2C3C4D1D2D3D4]
F′＝[Fcosτ+G+H 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0]T
α1＝α10＝16-4K
α2＝-16s2+16-3K
α3＝α7＝α12＝α16＝-64s2+16-4K
α4＝α8＝α13＝α17＝-144s2+16-4K
α5＝α9＝α14＝α18＝-256s2+16-4K
α6＝α11＝-16s2+16-2K
α15＝-16s2+16-6K
β1＝β9＝32ξs2
β2＝β10＝64ξs2
β3＝β11＝96ξs2
β4＝β12＝128ξs2
β5＝β13＝-32ξs2
β6＝β14＝-64ξs2
β7＝β15＝-96ξs2
β8＝β16＝-128ξs2
According to the result of the vibration response equation (5), the constant excitation has a great influence on the amplitudes of the main formants and the super-harmonic formants of the rotor system, wherein the response amplitude of the super-harmonic formants is positively correlated with the constant excitation, and the action direction of the constant excitation has a great influence on the response of the main formants of the system, but has a small influence on the response of the super-harmonic formants. This suggests that constant excitation may be a means of crack fault detection for aircraft engine rotor systems.
Other steps and parameters are the same as those in the second embodiment.
The fourth concrete implementation mode: the present embodiment is different from the first, second, or third embodiment in that the target control interval of the rotation speed in the second step is set as follows:
using 1/3, 1/2 of critical rotation speed as median of target interval, namely usingAndas target control intervals of the rotating speed, and applying coefficient control to the target control intervals; ω z is the critical speed and q is the deviation.
In industrial process control, because a controlled variable usually has the characteristics of a plurality of intermediate state variables, or a process is usually multi-variable coupling, a corresponding control method, namely a zone control strategy, is adopted in each zone. In order to enable the response of the target interval to be more obvious and improve the crack fault detection success rate, an interval control strategy is applied to a crack model of the rotor system. Under the action of constant excitation, coefficient control is applied to the target interval to enhance or weaken the vibration response.
The rotor system under the action of constant excitation generates larger amplitude response at 1/3, 1/2 and 1 time of the critical rotating speed, so the reference value of the target interval is as follows: to be provided withThe median of the target interval, with a deviation of + -q, i.e. As target control sections of the rotation speed, and coefficient control is applied to them.
Other steps and parameters are the same as those in the first, second or third embodiment.
The fifth concrete implementation mode: in the present embodiment, the value of the deviation q is 1/20 of the critical rotation speed ω z, which is different from the fourth embodiment.
Before control is applied, a rough value of the critical rotating speed of the aeroengine rotor system needs to be calculated. The method for calculating the critical rotating speed can adopt a matrix iteration method, a piecewise deduction algorithm, an energy method and the like, and the method for calculating the critical rotating speed of the dual-rotor system can adopt various improved algorithms based on a transfer matrix method, such as a substructure transfer matrix method, a transfer matrix-impedance coupling method, a split-mode-modal synthesis method and the like.
Other steps and parameters are the same as those in the fourth embodiment.
Examples
The following examples were used to demonstrate the beneficial effects of the present invention:
the rotor crack fault detection method based on the interval control strategy is carried out according to the following steps:
taking a certain type of aircraft engine as an example, a double-rotor system of the aircraft engine adopts a six-point supporting structure, wherein a high-pressure rotor system is of a two-fulcrum structure and adopts a supporting mode of 1-0-1; the low-pressure rotor system is of a four-pivot structure and adopts a 1-2-1 supporting mode. And then establishing an accurate complex dynamic discrete model comprising a 8-stage high-pressure compressor wheel disc, a 4-stage low-pressure compressor wheel disc, a 1-stage high-pressure turbine wheel disc and a 1-stage low-pressure turbine wheel disc. The low pressure part is selected to build a model of the single rotor system, as shown in fig. 1.
The crack response characteristics of the single rotor system in a noise-free and noisy environment in an uncontrolled natural state are shown in fig. 3 and 4; in the actual rotor crack detection process, various noise signals such as thermal noise and the like often exist in the environment where a rotor system is located, and the influence of the noise signals on the amplitude-frequency response curve of the rotor cannot be simply ignored, so that the disturbance influence of the noise must be added into a model. The noise is white gaussian noise, the variance is set to 1, and the mean is set to 0. And selecting a moving average filter to filter the response curve. It can be seen from fig. 3 that the rotor system also has a super-harmonic response under the effect of gravity alone without the influence of noise signals. This is because rotor gravity can also be considered a constant excitation, but the excitation is relatively small, so the over-harmonic response peak is much smaller than the main resonance peak, especially at quarter critical speed, which is hardly observed. It can be seen from fig. 4 that, after the addition of the noise effect, no significant over-harmonic response is visible in the amplitude-frequency response curve in the uncontrolled natural state, since the signal of the over-harmonic response is filtered out by the filter together with the noise signal.
Establishing a rotor system dynamic model, considering the action of external constant excitation, performing dynamic simulation on equation (3) under an interval control strategy, constructing a Simulink simulation program by using Matlab software, and performing rotor simulationThe system flow is shown in fig. 2, and in fig. 2, the zero-order harmonic component is: y is0＝A0、Z0＝C0；
The first harmonic component is:
the second order harmonic component is:
the third harmonic component is:
the fourth harmonic component is:
determining the critical speed omega in an uncontrolled natural statezDeviation of ωzAnd/20, then the rotating speed interval is pressed according to (omega)min,ωz-11)、(ωz–10，ωz+10)、(ωz+11，ωmax) The gravity force is divided into three parts, namely five times gravity force, twenty times gravity force and five times gravity force are applied respectively. The matrix results obtained in the same direction for each interval are connected in series, the relevant parameters of the rotor system are used as the input signals of the system, the vibration response of the rotor system is used as the output signals of the system, and the amplitude-frequency response characteristic of the single-rotor system is shown in fig. 5 and 6.
As can be seen from fig. 5: after applying constant excitation of 5 times gravity in the target interval, the signal of the super-harmonic response formant is obviously amplified, wherein the super-harmonic response at the quarter critical rotating speed can be obviously observed, and the signal of the super-harmonic response at the third critical rotating speed and the half super-harmonic response signal are amplified by 4.6 times compared with the uncontrolled natural state and basically reach the same order of magnitude as the main formant. It can be seen that the method has a significant amplification effect on the characteristic signal of the super-harmonic response of the crack region of the rotor compared with a single constant excitation.
As can be seen in fig. 6: in a noise environment, a formant of the over-harmonic response can still be obviously observed in an amplitude-frequency response curve under the interval control strategy. This shows that the method of the invention still has good amplification of the response of the crack region under the influence of noise. Therefore, if the invention can be applied to the early detection of actual cracks, the response of the crack area is more prominent, which is beneficial to detection, so as to repair or replace parts in time, and effectively reduce the accident rate.
The present invention is capable of other embodiments and its several details are capable of modifications in various obvious respects, all without departing from the spirit and scope of the present invention.
Claims (5)
1. The rotor crack fault detection method based on the interval control strategy is characterized by comprising the following steps:
selecting a low-pressure part of a double-rotor structure of an aircraft engine to establish a single-rotor system model, and establishing a coordinate system; the coordinate system takes an end point of the coincidence of the rotor and the mass center of the aircraft as an origin o, the x axis of the coordinate system is parallel to the longitudinal axis of the fuselage of the aircraft and points to the advancing direction of the aircraft, the oy axis is positioned in the symmetrical plane of the aircraft, is vertical to the ox axis and points right above the aircraft, and the oz axis, the ox axis and the oy axis form a right-hand coordinate system;
calculating the critical rotating speed of the rotor system of the aircraft engine, and setting a target control interval of the rotating speed according to the critical rotating speed;
step three, applying constant excitation in a target control interval of the Y-axis direction and the rotating speed of the position to be detected, and establishing a rotor system dynamic model;
step four, converting the rotor system dynamic model into a vibration response equation;
fifthly, taking each parameter as an input signal of the rotor system, taking the vibration response as an output signal of the rotor system, and drawing an amplitude-frequency response curve;
and step six, judging the crack fault of the rotor according to the amplitude-frequency response curve in the step four.
2. The interval control strategy-based rotor crack fault detection method according to claim 1, wherein the rotor system dynamics model in step three is specifically:
wherein m is the mass of the turntable, c is the damping, c is 2 ξ m omega, ξ is the damping ratio, omega is the rotating speed, △ k is the crack rigidity and shows the influence of the crack depth on the rigidity of the rotating shaft, k is the supporting rigidity of the rotor system, y is the y-axis coordinate of the center of mass of the turntable, first and second derivatives of y, respectively; t is time, and z is the z-axis coordinate of the center of mass of the turntable; e is the distance from the eccentric position of the turntable to the center of mass of the turntable, and g is the gravity acceleration; f. ofmIs an applied constant excitation.
3. The method for detecting the rotor crack fault based on the interval control strategy as claimed in claim 2, wherein the specific process of converting the rotor system dynamic model into the vibration response equation in step four comprises:
fourthly, carrying out dimensionless transformation on the rotor system dynamic model:
wherein, delta, s, tau and K, Y, Z are intermediate variables; omeganIs the system natural frequency; f represents the influence of unbalanced excitation force, G represents the influence of gravity, H represents the influence of external constant excitation, and the numerical value represents the multiple of the external constant excitation relative to the gravity;
then there are:
wherein,first and second derivatives of Y respectively,first and second derivatives of Z, respectively;
step four, solving the formula (1) by using a harmonic balance method:
let the solution of equation (3) be:
wherein A isi、Bi、Ci、DiIs the undetermined coefficient; i is 0,1, …, 4;
step four and three, bringing the formula (4) into the formula (3), and enabling the sum of the coefficients of the harmonics to be zero to obtain the vibration response equation:
A＝R-1*F′ (5)
wherein A ═ A1A2A3A4B1B2B3B4C0C1C2C3C4D1D2D3D4]
F′＝[Fcosτ+G+H 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0]T
α1＝α10＝16-4K
α2＝-16s2+16-3K
α3＝α7＝α12＝α16＝-64s2+16-4K
α4＝α8＝α13＝α17＝-144s2+16-4K
α5＝α9＝α14＝α18＝-256s2+16-4K
α6＝α11＝-16s2+16-2K
α15＝-16s2+16-6K
β1＝β9＝32ξs2
β2＝β10＝64ξs2
β3＝β11＝96ξs2
β4＝β12＝128ξs2
β5＝β13＝-32ξs2
β6＝β14＝-64ξs2
β7＝β15＝-96ξs2
β8＝β16＝-128ξs2。
4. The method for detecting the rotor crack fault based on the interval control strategy as claimed in the claim 1, 2 or 3, characterized in that the target control interval of the rotating speed in the step two is set as follows:
using 1/3, 1/2 of critical rotation speed as median of target interval, namely usingAndas target control intervals of the rotating speed, and applying coefficient control to the target control intervals; omegazThe critical speed is q, and q is the deviation.
5. The interval control strategy-based rotor crack fault detection method according to claim 4, wherein the value of the deviation q is a critical rotation speed ωz1/20 of (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910403658.XA CN110134110A (en) | 2019-05-15 | 2019-05-15 | Rotor crack fault detection method based on range restraint strategy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910403658.XA CN110134110A (en) | 2019-05-15 | 2019-05-15 | Rotor crack fault detection method based on range restraint strategy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110134110A true CN110134110A (en) | 2019-08-16 |
Family
ID=67574306
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910403658.XA Pending CN110134110A (en) | 2019-05-15 | 2019-05-15 | Rotor crack fault detection method based on range restraint strategy |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110134110A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111219210A (en) * | 2020-01-08 | 2020-06-02 | 西北工业大学 | Dynamics optimization design method based on reverse rotation double-rotor whirling direction reversing |
| CN114485915A (en) * | 2022-01-08 | 2022-05-13 | 西北工业大学 | Method for establishing three-dimensional expression mode of response characteristic of double-rotor system |
| CN114912494A (en) * | 2022-06-07 | 2022-08-16 | 武汉科技大学 | Rotating shaft fatigue crack positioning method driven by super-harmonic dynamic mode |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008149803A (en) * | 2006-12-15 | 2008-07-03 | Bridgestone Corp | Method and device for sensing tire failure, and tire for sensing failure inside tire |
| CN101532911A (en) * | 2009-04-24 | 2009-09-16 | 华北电力大学 | Large steam turbine-generator set rotor crack fault real-time diagnosis method |
| CN102980944A (en) * | 2012-11-13 | 2013-03-20 | 上海交通大学 | System and method for rotor system on-line health monitoring |
| CN103592365A (en) * | 2013-11-14 | 2014-02-19 | 西安交通大学 | Rapid rotor crack detection method |
| CN107389732A (en) * | 2017-07-14 | 2017-11-24 | 中国计量大学 | A kind of laser scanning thermal imaging crack detecting method |
| CN108427857A (en) * | 2018-04-11 | 2018-08-21 | 浙江师范大学 | A kind of rotor variation rigidity based on the arbitrary shear crack in space determines method and system |
| CN109253882A (en) * | 2018-10-08 | 2019-01-22 | 桂林理工大学 | A kind of rotor crack fault diagnostic method based on variation mode decomposition and gray level co-occurrence matrixes |
-
2019
- 2019-05-15 CN CN201910403658.XA patent/CN110134110A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008149803A (en) * | 2006-12-15 | 2008-07-03 | Bridgestone Corp | Method and device for sensing tire failure, and tire for sensing failure inside tire |
| CN101532911A (en) * | 2009-04-24 | 2009-09-16 | 华北电力大学 | Large steam turbine-generator set rotor crack fault real-time diagnosis method |
| CN102980944A (en) * | 2012-11-13 | 2013-03-20 | 上海交通大学 | System and method for rotor system on-line health monitoring |
| CN103592365A (en) * | 2013-11-14 | 2014-02-19 | 西安交通大学 | Rapid rotor crack detection method |
| CN107389732A (en) * | 2017-07-14 | 2017-11-24 | 中国计量大学 | A kind of laser scanning thermal imaging crack detecting method |
| CN108427857A (en) * | 2018-04-11 | 2018-08-21 | 浙江师范大学 | A kind of rotor variation rigidity based on the arbitrary shear crack in space determines method and system |
| CN109253882A (en) * | 2018-10-08 | 2019-01-22 | 桂林理工大学 | A kind of rotor crack fault diagnostic method based on variation mode decomposition and gray level co-occurrence matrixes |
Non-Patent Citations (2)
| Title |
|---|
| 侯磊: "《一类两自由度参激系统在常数激励下的响应研究》", 《物理学报》 * |
| 侯磊: "《激动飞行环境下转子系统的非线性动力学行为研究》", 《中国优秀硕士学位论文全文数据库 工程科技II辑》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111219210A (en) * | 2020-01-08 | 2020-06-02 | 西北工业大学 | Dynamics optimization design method based on reverse rotation double-rotor whirling direction reversing |
| CN114485915A (en) * | 2022-01-08 | 2022-05-13 | 西北工业大学 | Method for establishing three-dimensional expression mode of response characteristic of double-rotor system |
| CN114485915B (en) * | 2022-01-08 | 2023-07-04 | 西北工业大学 | Method for establishing three-face three-dimensional expression mode of response characteristic of double-rotor system |
| CN114912494A (en) * | 2022-06-07 | 2022-08-16 | 武汉科技大学 | Rotating shaft fatigue crack positioning method driven by super-harmonic dynamic mode |
| CN114912494B (en) * | 2022-06-07 | 2024-11-01 | 武汉科技大学 | Method for positioning fatigue crack of rotating shaft driven by super-harmonic dynamics mode |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110134110A (en) | Rotor crack fault detection method based on range restraint strategy | |
| Huang et al. | Designing active flutter suppression for high-dimensional aeroelastic systems involving a control delay | |
| Pan et al. | A review on self-recovery regulation (SR) technique for unbalance vibration of high-end equipment | |
| Zhang et al. | New active online balancing method for grinding wheel using liquid injection and free dripping | |
| CN107092750B (en) | Nonlinear dynamics modeling method for gear tooth damage fault of internal gear shaft speed reducer | |
| Zhao et al. | Nonlinear analysis of a dual-disk rotor system considering elastoplastic contact | |
| Lu et al. | Dynamic modeling and bifurcation analysis of blade-disk rotor system supported by rolling bearing | |
| Fu et al. | Imbalance–misalignment–rubbing coupling faults in hydraulic turbine vibration | |
| Prasad et al. | Analysis of classical flutter in steam turbine blades using reduced order aeroelastic model | |
| Modorskii et al. | Research of aerohydrodynamic and aeroelastic processes on PNRPU HPC system | |
| Gao et al. | Nonlinear finite element modeling and vibration analysis of the blisk deposited strain-dependent hard coating | |
| Mekhonoshina et al. | Numeric simulation of the interaction between subsonic flow and a deformable profile blade on the compressor experiment phase | |
| Wang et al. | Research on model-free adaptive control of electro-hydraulic servo system of continuous rotary motor | |
| Shi et al. | Speed fluctuation suppression by model-based feed-forward control in gimbal system with harmonic drive | |
| Willeke et al. | Reduced order modeling of mistuned bladed disks considering aerodynamic coupling and mode family interaction | |
| Liu et al. | Flap/Lag Stall Flutter Control of Large‐Scale Wind Turbine Blade Based on Robust H2 Controller | |
| Chen et al. | Homotopy analysis method for limit cycle oscillations of an airfoil with cubic nonlinearities | |
| Li et al. | Research on decoupling control for electro-hydraulic load simulator | |
| Tan et al. | Development of wind tunnel dynamic test system for coupled motion with multi-degrees of freedom | |
| Qian et al. | Flutter control of a two-dimensional airfoil using wash-out filter technique | |
| Liao et al. | Dynamic Simulation Analysis of Aircraft Hydraulic Pipeline System under Different Pressure | |
| Yan et al. | An ADRC Strategy With Sequential Output Stacking Extended State Observers to Evaluate Hydraulic Torque for a Continuous-Wave Pulse Generator | |
| Asdaque et al. | Vibration analysis of multi-disk multi-profiled shaft-rotor systems | |
| Baogui et al. | Study on vibration characteristics of plastic helical gear assembly with prestress | |
| Liu et al. | Modeling and key technologies study of three-stage electro-hydraulic servo valve |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190816 |