CN1364998A - Monitoring and diagnosing method for the gap between defective vanes of vane machine - Google Patents
Monitoring and diagnosing method for the gap between defective vanes of vane machine Download PDFInfo
- Publication number
- CN1364998A CN1364998A CN 02113373 CN02113373A CN1364998A CN 1364998 A CN1364998 A CN 1364998A CN 02113373 CN02113373 CN 02113373 CN 02113373 A CN02113373 A CN 02113373A CN 1364998 A CN1364998 A CN 1364998A
- Authority
- CN
- China
- Prior art keywords
- blade
- pulse
- signal pulse
- turbomachine
- fault
- 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.)
- Granted
Links
Images
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Control Of Turbines (AREA)
Abstract
The monitoring and diagnosing process of vane disturbance of vane wheel machine includes rotating vane wheel machine, selecting from computer "program" the vane interval monitoring and diagnosing software for vane disturbance of vane wheel machine and displaying the main frame, pushing the diagnosis button, inputting the vane number of tested vane wheel machine, determining vane type, amplifying and filtering vane pulse signal and phase discriminating signal before feeding to computer; display vane signal pulse diagram, phase discriminating signal diagram and disturbance diagnosis diagram to find, analyze and judge vane fault. The present invention has high reliability and high measurement precision, and may be used for monitoring and diagnosing fault vane interval in various vane wheel machine.
Description
Technical field
The present invention relates to a kind of monitoring, diagnosing method of turbomachine blade fault.This method is utilized sensor non-cpntact measurement adjacent two interlobate spacings, and the spacing of being surveyed is carried out analyzing and processing, extracts the blade fault feature, and whether differentiate blade has fault, fault type, the fault order of severity, and carries out the blade fault forecast.This method mainly is applicable to all kinds of turbomachine optimal design, performance evaluation, operation monitoring and fault diagnosis.
Background technology
Turbomachine is to utilize blade to carry out a kind of rotating machinery that mechanical energy and fluid can be changed mutually, as: the steam turbine of generating plant, the hydraulic turbine, the turbocompressor of aircraft, turbine engine, the compressor in chemical plant, the ventilation blower of underground mining, water pump etc.Turbomachine is the emphasis key equipment that is widely used in all trades and professions, and blade is the critical component of turbomachine, bears the combined action of centrifugal force, hydrodynamic force, vibration, the temperature difference (thermal stress), medium etc.Turbomachine just develops towards heavy loading, high speed, lightness direction now, and blade working length and running parameter are improved constantly, and condition of work is more and more harsher, causes blade to break down easily.Have data to show that blade fault accounts for more than 65% of turbomachine fault, and the accident that blade fault causes is catastrophic often, can cause tremendous loss.Blade fault has a strong impact on the economy and the safe operation of turbomachine.As simpler method how and higher accuracy rate online in real time forecast blade fault, be the difficult problem of domestic and international equipment fault diagnosis engineering circle of puzzlement and academia.
In the data that retrieves, former Soviet Union Ba Lanuofu Academia Sinica proposes the interruption phase method of monitoring blade vibration at present.Rotating vane will produce deformation under the effect of powerful windage resistance, the windage resistance of variation and the acting in conjunction of blade elastic restoring force make blade produce vibration with respect to the turbomachine rotating shaft, and its amplitude is more stable.When blade had had small fatigue crack or other fault, the amplitude of blade can obviously raise.Being interrupted the phase place ratio juris is to measure the sweep length that blade tip entered and left pulse transducer.These pulse transducers are mounted on the corresponding shell of turbomachine blade, and when blade pass extra pulse sensor, pulse transducer will produce pulse, analyze the information of relevant blade vibration situation then from these pulse widths.Adopt when being interrupted the phase method test, when blade is in normal condition, occur the waveform of rule on the oscillograph; Blade vibration, when fractureing, phase differential will appear in the signal of pulse transducer output, be embodied in fault before and after the blade sweep length change, ray length can change on this moment oscillograph, can judge the size of blade vibration thus.Can diagnose blade fault according to the blade vibration information that the interruption phase method obtains.
The key step of being interrupted phase method is: use sensor acquisition blade vibration amplitude signal with respect to rotation axis under dynamically; Enter sensor from certain blade and begin to produce pulse, this pulse signal is input on the vertical plates of electron ray tube, makes ray along shielding displacement and beginning to draw vertical scan line, when this blade leaves sensor, pulse disappears, and ray stops to move and finishing the drafting of vertical scan line; Determine the amplitude of blade vibration according to the length of ray on the screen, judge the blade fault form by the vibration information that measures.
Be interrupted phase method following deficiency is arranged: appearance can reflect truly that the probability of peak swing is very low.Because can produce the condition of maximum sweep width be: along sense of rotation, blade enters the sensor scan district when being the forward maximum displacement, and simultaneously, along sense of rotation, blade leaves the sensor scan district when being reverse maximum displacement, but it is very low the probability of above condition to occur; Can not distinguish blade vibration and blade fault.Because the difference of working conditions change and blade individuality causes each blade amplitude that certain difference is arranged, so can not from the amplitude that test obtains, tell the amplitude that blade is normal and blade fault produces with being interrupted phase method; The blade vibration parameter be can only measure, monitoring, diagnosing deformable blade, bending, loosening are not suitable for.
The device that the present invention uses comprises:
1, blade pulse transducer: as Beijing vibration measuring instrument plant 8500 serial current vortex sensors, model: 85811-01A-85745
-01A。
2, fore-lying device: as Beijing vibration measuring instrument plant 8500 serial current vortex sensor φ 8 probe fore-lying devices, model: 85811-01A.
3, A/D card: as American National Instrument Instruments company product, model: DAQCARD-1200.
4, computing machine: as the U.S.'s H500XT of Dell company notebook or medium-to-high grade PC.
5, stube cable: produce model: RVVP4 * 0.2 signal shielding cable or other shielded cable as Chongqing cable factory.
6, phase discriminating pulse sensor: as Beijing vibration measuring instrument plant 8500 serial current vortex sensors, model: 85811-01A-85745
-01A。
7, D.C. regulated power supply; Produce model: 4NIC-X24 as Chaoyang city power supply company limited.
The formation of this device is: radially on the shell pulse transducer is installed at turbomachine, sensor probe is aimed at turbomachine with all blades on the one-level, and the probe distance vane tip is 1～2mm; The keeper of a phase discriminating pulse sensor is installed above the main shaft external profile diameter direction of impeller, and this keeper will align with the wherein blade on the impeller, and the leaf marking corresponding with this keeper is a blade.The phase discriminating pulse sensor is installed above keeper, and the probe of phase discriminating pulse sensor and the distance between the keeper are 1～2mm; The cable that carries with sensor is connected sensor with fore-lying device, with fore-lying device and A/D card connection, the A/D card inserts computer slot with stube cable; With stube cable with on the D.C. regulated power supply ± 15 volts of power supplys are connected with fore-lying device.
Summary of the invention
The objective of the invention is deficiency, propose spacing monitoring, diagnosing method between a kind of turbomachine blade fault leaf at existing method.This method can be avoided requiring pulse transducer to produce maximum sweep width when monitoring; Can distinguish blade vibration and blade fault, and the normal vibration value is got rid of outside detected value; Can diagnose reliably common blade fault form.
Spacing monitoring, diagnosing ratio juris is between turbomachine blade fault leaf: consider the variation that will cause spacing between the blade after blade breaks down.And the variation of spacing can reflect with the wide variety between the detected pulse of pulse transducer between blade, the blade signal pulse that produces when therefore adopting the blade pulse transducer non-cpntact measurement rotating vane that is installed on the turbomachine shell to pop one's head in through the blade pulse transducer, with the spacing between this signal pulse detection adjacent blades, utilize simultaneously the phase discriminating pulse sensor to the phase discrimination signal pulse carry out number of blade segmentation, reach purpose, make between leaf dynamic space corresponding one by one with blade to spacing calibration between leaf.In the continuous operation process of turbomachine, impeller revolves and turns around that spacing is a sample between detected leaf, handles by the data to multisample, and the information of blade vibration and blade fault is obtained in the variation of the dynamic space that analytical calculation is interpulse.When blade did not have fault, two interlobate spacings were fixed, and the spacing between the signal pulse that the blade pulse transducer produces is uniform.And blade is when breaking down, and the spacing between pulse signal can change.Therefore, by performance analysis, can judge the running status of blade and diagnose blade fault the signal pulse spacing.
Consider that blade vibration also will cause the variation of dynamic space between the blade, but the characteristics that dynamic space changes between blade vibration and the caused leaf of blade fault are different, therefore can distinguish blade vibration and blade fault.For rigid blade, the variation of the dynamic space that causes with respect to blade fault, the variation of the dynamic space that blade vibration causes is negligible.For flexible blade, the variation of the dynamic space that causes with respect to blade fault, the variation of the dynamic space that blade vibration causes is bigger.Under rotating speed height, the big condition of loading, the rigid blade on some turbomachine becomes flexible blade, otherwise the flexible blade on some turbomachine becomes rigid blade.
In order to realize the foregoing invention purpose, technology implementation scheme of the present invention is:
1, starts actuating unit, turbomachine is rotated;
Spacing monitoring, diagnosing software between the turbomachine blade fault leaf in 2, startup computing machine, and operation the Start menu under " program " option;
3, computing machine shows the key frame of this software;
4, click on the key frame button that name is called " spacing monitoring, diagnosing method between leaf " with left mouse button;
5, the lobe numbers of the tested turbomachine of input is with left mouse button click OK button;
6, select rigid blade or flexible blade, and with left mouse button click OK button;
7, blade signal pulse and the pulse of phase discriminating pulse sensor acquisition phase discrimination signal that spacing changes between blade pulse transducer collection reflection adjacent blades makes these two kinds of signal pulses enter fore-lying device automatically, and fore-lying device is sent into computing machine after to its amplification, Filtering Processing;
8, computing machine is according to the signal that transmits from fore-lying device, automatically show that turbomachine begins the time dependent blade signal pulse of the pulse signal figure of monitored back each blade of turbomachine, the time dependent phase discrimination signal pulse diagram of pulse that phase discriminating pulse sensor keeper produces and each blade rotation one circle on the tested turbomachine, the signal pulse that the blade pulse transducer produces is one group of blade signal pulse, rotate the n circle, form n group blade signal pulse, the blade fault diagnosing figure that n group blade signal pulse and the pulse of segmentation phase discrimination signal constitute.The segmentation phase discrimination signal pulse of each blade correspondence is to obtain after subtracting 1 by the double pulse width that produces by the phase discriminating pulse sensor of phase discriminating pulse sensor keeper divided by the number of blade of turbomachine, with these all blade signal pulses that each blade is produced with to segment the phase discrimination signal pulse accordingly corresponding;
For rigid blade because not vibration of rigid blade, when blade does not have fault, the segmentation phase discrimination signal pulse corresponding of all signal pulse of this blade with it on same straight line, X at this moment
IjApproach zero.When certain blade had produced fault, what all cause the blade signal pulse to some extent shifted to an earlier date or hysteresis X
IjBe not equal to zero, X
IjBig more, fault is serious more.To X
IjSet failure warning value T, as benchmark, computing machine carries out trend analysis.When | behind Xij| 〉=T, computing machine is reported to the police.T is by formula according to the importance of institute's monitoring equipment, rotating speed height
And specifically determine.
For flexible blade, whether blade fault takes place all will produce blade vibration.When blade did not have fault, the segmentation phase discrimination signal pulse corresponding with it of this blade signal pulse be not on same straight line, and the blade pulse is paced up and down X about the segmentation phase discrimination signal pulse position of its correspondence
IjBe not equal to zero, X
IjMean value
Approach zero.The Oscillation Amplitude F of blade equals the X in repeatedly the measuring of this blade
IjMaximal value max{X
IjAnd minimum value min{X
IjDifference.When blade breaks down, X
IjMean value G be not equal to zero, mean value G is big more, and the fault that shows is serious more.Distinguish blade vibration and blade fault with this.Importance, rotating speed height according to institute's monitoring equipment are set failure warning value T to G, simultaneously Oscillation Amplitude F is set vibratory alarm value W, W determines according to relevant corresponding turbomachine blade vibration national standard, carries out trend analysis and warning as reference computer;
Wherein: X
Ij---the signal pulse of j sheet blade occurred with the pulse of segmentation phase discrimination signal when turbomachine rotated the i circle
Time difference,
The number of turns numbering of i---blade rotation, i=1,2 ... n,
N---the actual number of turns of wheel rotation during test,
J---blade number, j=1,2 ... m,
M---actual lobe numbers,
The maximum of s---blade tip allows deflection,
K---blade safety coefficient is looked into national standard and is determined,
ω---the angular velocity of turbomachine rotation,
R---blade tip is to the distance at rotating shaft center.
9, observe trouble-shooting chart, and fault is carried out analysis and judgement.When the blade signal pulse complete obiteration of blade, just can diagnose this turbomachine generation blade broken or break.
For rigid blade,, appear at the right of segmenting the phase discrimination signal pulse at trouble-shooting chart blade signal pulse, at this moment X when a large amount of blade signal pulses position of blade lags behind with respect to segmentation phase discrimination signal pulse position
IjGreater than zero, can tentative diagnosis go out the turbomachine deformable blade.When a large amount of blade signal pulses position of blade shifts to an earlier date with respect to segmentation phase discrimination signal pulse position, appear at the left side of segmenting the phase discrimination signal pulse at trouble-shooting chart blade signal pulse, at this moment X
IjLess than zero, then can the loosening or deformable blade of blade be arranged the tentative diagnosis turbomachine;
To flexible blade, the position after a large amount of blade signal pulses of blade are average always shifts to an earlier date with respect to segmentation phase discrimination signal pulse position, and this moment, G was less than zero, just can have blade to become flexible or deformable blade by the tentative diagnosis turbomachine.Position behind a large amount of blade average pulses of blade lags behind with respect to segmentation phase discrimination signal pulse position, and this moment, G was greater than zero, then can deformable blade be arranged the tentative diagnosis turbomachine;
10, close turbomachine, open casing and confirm failure mode, when turbomachine does not have fault, continuous monitoring.
This method compared with prior art has following technique effect:
Reliability height when (1) measuring.Because method of the present invention is that spacing between blade is monitored, do not need directly to detect the situation of change of each blade, do not produce maximum sweep width so require sensor.Avoided wanting sensor to produce maximum sweep width and in the reality sensor can produce very little this contradiction of probability of maximum sweep width.Thereby improved reliability.
(2) the blade fault kind that can diagnose out is many.The blade fault kind that this method can be diagnosed out fractures, breaks, is out of shape, becomes flexible.And the interruption phase method can only detect the relevant vibration parameters of blade.
(3) monitoring accuracy height.In laboratory examination, utilize the blade rotor experiment table to carry out monitoring, diagnosing, its as a result rate of accuracy reached to 90%-100%.Result by Figure 14 shows: when the turbomachine that is made of 6 blades is tested, occur when loosening as 5 blades, detect and diagnose out 5 blade generation blades loosening; When 4 bending blades, detect and diagnose out 4 blade generation bending blades; When fractureing appears in a slice blade, detect and diagnose out 1 blade to fracture.And the position is accurate, test rate of accuracy reached to 100%.When the turbomachine that is made of 12 blades is tested, occur when loosening, detect and diagnosed out 6 blades wherein loosening as 7 blades; Occur when crooked as 1 blade, detect and diagnosed out 1 blade to bend; When 2 blade brokens, detect and diagnosed out 2 blades to fracture.And the position is accurate, its rate of accuracy reached to 90%.And strict differentiation blade vibration of this method energy and blade fault, thereby accuracy rate is increased greatly.
(4) be easily understood, only need remember blade signal pulse position and the corresponding concrete failure mode of segmentation phase discrimination signal pulse position relationship characteristic on the trouble-shooting chart, just can diagnose the turbomachine blade fault.
(5) realize not needing complicated custom-designed monitoring diagnosis device just can realize the monitoring, diagnosing of turbomachine blade fault easily.
Description of drawings
Spacing monitoring, diagnosing method test philosophy figure between Fig. 1 leaf,
Fig. 2 blade rotor experiment table structural representation,
Fig. 3 blade rotor experiment table stereographic map,
Fig. 4 rigid blade fault diagnosis synoptic diagram,
Fig. 5 flexible blade fault diagnosis synoptic diagram,
The blade signal pulse figure of the blade rotor experiment table that 6 rigid blades of Fig. 6 are formed,
Fig. 7 phase discrimination signal pulse diagram,
It is the blade signal pulse figure behind the blade that Fig. 8 takes off label,
The trouble-shooting chart of blade rotor experiment table under normal operation that 6 rigid blades of Fig. 9 are formed,
The blade rotor experiment table that 6 rigid blades of Figure 10 are formed is the trouble-shooting chart behind the blade taking off label,
The trouble-shooting chart of blade rotor experiment table under normal operation that 6 flexible blades of Figure 11 are formed,
The blade rotor experiment table that 6 flexible blades of Figure 12 are formed is No. three trouble-shooting charts under the bending blade situation at label,
Spacing monitoring, diagnosing software flow pattern between Figure 13 turbomachine blade fault leaf,
Figure 14 is by 6 or 12 blade rotor testing table partial fault diagnostic result figure that blade is formed,
In Fig. 1 to Fig. 2
1, casing 7, computing machine
2, blade 8, bearing seat
3, rotor 9, bearing
4, screw 10, support
5, pulse transducer 11, motor
6, fore-lying device
Embodiment
In order to verify the present invention, constructed the blade rotor experiment table in the laboratory.This experiment table is installed two bearings on support, in order to support and to fix two bearing seats, on two bearing seats, rotating shaft is installed, one end of rotating shaft is connected with motor by shaft coupling, an impeller is installed by the central authorities of rotating shaft, every 15 degree, the threaded hole that promptly processes M6 in order to install blade 24 branches such as grade on impeller.The material of blade is 45 steel, uniform cross section, and thickness 1mm, width are 15mm, and flexible blade working portion height is 25cm, and rigid blade working portion height is 10cm.Motor is a threephase asynchronous, power 3.5KW, and by frequency converter timing, the motor speed variation range is 0～12000r/min.
1,6 rigid blades are installed on the blade rotor experiment table, the concrete monitoring, diagnosing step of rigid blade is as follows:
(1) Input Software password aaaa.
(2) prompting input turbomachine lobe numbers on the computer screen, input digit 6 is with left mouse button click OK button.
(3) click the button of " rigid blade " by name with left mouse button, enter spacing monitoring, diagnosing between the rigid blade leaf.
(4) blade signal pulse figure, phase discrimination signal pulse diagram and the trouble-shooting chart of 6 blades of demonstration.Spacing between the pulse on the blade signal pulse figure of this moment is even.Show three pulse signals on the phase discrimination signal pulse diagram.X on the trouble-shooting chart
1The first lap of 6 blades, in like manner X are measured in expression
2, X
3, X
4, X
5Represent the measurement of the 2nd, 3,4,5 circles that the blade rotor experiment table rotates respectively, each triangle symbol of figure upper bottom portion represents to segment the pulse that phase discrimination signal produces, other triangle symbol is represented the signal pulse that every blade pass produces when crossing blade pulse transducer probe, the numbering of corresponding 6 blades of the sequence number at figure top.
(5) COMPUTER CALCULATION X
IjValue equal 0, observe trouble-shooting chart, find out every blade on the trouble-shooting chart in each blade signal pulse that produces during by the blade pulse transducer and each self-corresponding segmentation phase discrimination signal pulse all on same straight line, blade does not have fault.
(6) click " stop sampling " button on the interface with left mouse button.
(7) click the Close button in the upper right corner, interface with left mouse button, withdraw from spacing monitoring, diagnosing software systems between turbomachine blade fault leaf.
(8) click " closing " option in the Start menu with left mouse button, shut down computer.
(9) cut off the electricity supply, impeller stops operating.
(10) take off first blade from impeller.
(11) repeated priming motor makes turbomachine turn to the process that blade signal pulse and phase discrimination signal pulse enter computing machine.
(12) show blade signal pulse figure, phase discrimination signal pulse diagram and trouble-shooting chart.There are two spacings between the blade pulse that obvious variation has taken place on the blade signal pulse figure of this moment, the complete obiteration of a blade signal pulse has been arranged.Can initial analysis going out according to the pulse on the phase discrimination signal pulse diagram simultaneously is that first blade may fracture or break.Observe trouble-shooting chart, the blade pulse complete obiteration of first blade, i.e. X
I1For infinity, judge that tentatively the number one blade fractures or break.
(13) COMPUTER CALCULATION X
IjValue, X
I1Value be infinitely great, computing machine sends chimes of doom.
(14) click " stop sampling " button on the interface with left mouse button.
(15) disable motor stops operating impeller.
(16) click the Close button in the upper right corner, interface with left mouse button, withdraw from spacing monitoring, diagnosing software between turbomachine blade fault leaf.
(17) click " closing " option in the Start menu with left mouse button, shut down computer.
All the other steps are identical with technical scheme.
2,6 flexible blades are installed on the blade rotor experiment table, the concrete monitoring, diagnosing step of flexible blade is as follows:
(1) repeated priming motor makes turbomachine turn to the process of the input number of blade.
(2) click the button of " flexible blade " with left mouse button, enter spacing monitoring, diagnosing between the flexible blade leaf.
(3) the phase discrimination signal pulse of the blade signal pulse that collects of blade pulse transducer and phase demodulation sensor acquisition enters computing machine through filtering, the processing and amplifying of fore-lying device.
(4) trouble-shooting chart of 6 flexible blades of demonstration.X on this trouble-shooting chart
1Represent the first lap that 6 flexible blades are measured, X is in like manner arranged
2, X
3, X
4, X
5Represent measurements respectively to the 2nd, 3,4,5 circles of whole turbomachine rotation, each triangle symbol of figure upper bottom portion represents to segment the pulse that phase discrimination signal produces, other triangle symbol is represented the pulse that every blade pass produces when crossing blade pulse transducer probe, the numbering of the corresponding blade of the sequence number at figure top.
(5) X of each blade correspondence of COMPUTER CALCULATION
IjMean value equal 0.Observe the trouble-shooting chart of 6 flexible blades, though find out every blade on the trouble-shooting chart in each blade signal pulse that produces during by the blade pulse transducer and each self-corresponding segmentation phase discrimination signal pulse not on same straight line, but they are always paced up and down about each self-corresponding segmentation phase discrimination signal pulse position, their mean place and each self-corresponding segmentation phase discrimination signal pulse position are on same straight line, and blade does not have fault.
(6) repeat the step that " stopping sampling " stops operating to impeller.
(7) make No. three blade tip bending.
(8) the repeated priming motor enters the step of computing machine to blade signal pulse and phase discrimination signal pulse.
(9) show trouble-shooting chart.Observe trouble-shooting chart, find out that the mean place segmentation phase discrimination signal pulse position corresponding with it of the blade signal pulse that No. three blades on the trouble-shooting chart produce compared hysteresis at every turn by blade sensor the time, No. three blade has bending blade.
(10) X of each blade correspondence of COMPUTER CALCULATION
IjMean value, wherein, the X of No. three blade
I3Mean value greater than 0, computing machine sends chimes of doom.
(11) repeat " stopping sampling " to the step of shutting down computer.
All the other steps are identical with technical scheme.
Claims (3)
1, spacing monitoring, diagnosing method between a kind of turbomachine blade fault leaf is characterized in that the step of this monitoring, diagnosing method is as follows:
(1) starts actuating unit, turbomachine is rotated;
Spacing monitoring, diagnosing software between the turbomachine blade fault leaf in (2) startup computing machine, and operation the Start menu under " program " option;
(3) computing machine shows the key frame of this software;
(4) click on the key frame button that name is called " spacing monitoring, diagnosing method between leaf " with left mouse button;
(5) lobe numbers of the tested turbomachine of input is with left mouse button click OK button;
(6) select rigid blade or flexible blade, and with left mouse button click OK button;
(7) blade signal pulse and the pulse of phase discriminating pulse sensor acquisition phase discrimination signal that spacing changes between blade pulse transducer collection reflection adjacent blades makes these two kinds of signal pulses enter fore-lying device automatically, and fore-lying device is sent into computing machine after to its amplification, Filtering Processing;
(8) computing machine is according to the signal that transmits from fore-lying device, automatically show that turbomachine begins the time dependent blade signal pulse of the pulse signal figure of monitored back each blade of turbomachine, the time dependent phase discrimination signal pulse diagram of pulse that phase discriminating pulse sensor keeper produces and each blade rotation one circle on the tested turbomachine, the signal pulse that the blade pulse transducer produces is one group of blade signal pulse, rotate the n circle, form n group blade signal pulse, the blade fault diagnosing figure that n group blade signal pulse and the pulse of segmentation phase discrimination signal constitute;
For rigid blade because not vibration of rigid blade, when blade does not have fault, the segmentation phase discrimination signal pulse corresponding of all signal pulse of this blade with it on same straight line, X at this moment
IjApproach zero.When certain blade had produced fault, what all cause the blade signal pulse to some extent shifted to an earlier date or hysteresis X
IjBe not equal to zero, X
IjBig more, fault is serious more, to X
IjSet failure warning value T, as benchmark, computing machine carries out trend analysis, when | behind Xij| 〉=T, computing machine is reported to the police, and T is by formula according to the importance of institute's monitoring equipment, rotating speed height
And specifically determine;
For flexible blade, whether blade fault takes place all will produce blade vibration, when blade did not have fault, the segmentation phase discrimination signal pulse corresponding with it of this blade signal pulse be not on same straight line, the blade pulse is paced up and down X about the segmentation phase discrimination signal pulse position of its correspondence
IjBe not equal to zero, X
IjMean value
Approach zero, the Oscillation Amplitude F of blade equals the X in repeatedly the measuring of this blade
IjMaximal value max{X
IjAnd minimum value min{X
IjDifference, when blade breaks down, X
IjMean value G be not equal to zero, mean value G is big more, and the fault that shows is serious more, distinguish blade vibration and blade fault with this, importance, rotating speed height according to institute's monitoring equipment are set failure warning value T to G, simultaneously Oscillation Amplitude F is set vibratory alarm value W, W determines according to relevant corresponding turbomachine blade vibration national standard, carries out trend analysis and warning as reference computer;
Wherein: X
Ij---the signal pulse of j sheet blade occurred with the pulse of segmentation phase discrimination signal when turbomachine rotated the i circle
Time difference,
The number of turns numbering of i---blade rotation, i=1,2 ... n,
N---the actual number of turns of wheel rotation during test,
J---blade number, j=1,2 ... m,
M---actual lobe numbers,
The maximum of s---blade tip allows deflection,
K---blade safety coefficient is looked into national standard and is determined,
ω---the angular velocity of turbomachine rotation,
R---blade tip is to the distance at rotating shaft center;
(9) observe trouble-shooting chart, and fault is carried out analysis and judgement,, just can diagnose this turbomachine generation blade broken or break when the blade signal pulse complete obiteration of blade;
For rigid blade,, appear at the right of segmenting the phase discrimination signal pulse at trouble-shooting chart blade signal pulse, at this moment X when a large amount of blade signal pulses position of blade lags behind with respect to segmentation phase discrimination signal pulse position
IjGreater than zero, can tentative diagnosis go out the turbomachine deformable blade, when a large amount of blade signal pulses position of blade shifts to an earlier date with respect to segmentation phase discrimination signal pulse position, appear at the left side of segmenting the phase discrimination signal pulse at trouble-shooting chart blade signal pulse, at this moment X
IjLess than zero, then can the loosening or deformable blade of blade be arranged the tentative diagnosis turbomachine;
To flexible blade, position after a large amount of blade signal pulses of blade are average with respect to segmentation phase discrimination signal pulse position in advance always, this moment, G was less than zero, just can the loosening or deformable blade of blade be arranged the tentative diagnosis turbomachine, position behind a large amount of blade average pulses of blade lags behind with respect to segmentation phase discrimination signal pulse position, this moment, G was greater than zero, then can deformable blade be arranged the tentative diagnosis turbomachine;
(10) close turbomachine, open casing and confirm failure mode, when turbomachine does not have fault, continuous monitoring.
2, spacing monitoring, diagnosing method between turbomachine blade fault leaf according to claim 1 is characterized in that the monitoring, diagnosing step of rigid blade is as follows:
(1) Input Software password aaaa;
(2) prompting input turbomachine lobe numbers on the computer screen, input digit 6 is with left mouse button click OK button;
(3) click the button of " rigid blade " by name with left mouse button, enter spacing monitoring, diagnosing between the rigid blade leaf;
(4) blade signal pulse figure, phase discrimination signal pulse diagram and the trouble-shooting chart of 6 blades of demonstration, the spacing between the pulse on the blade signal pulse figure of this moment is even, shows three pulse signals on the phase discrimination signal pulse diagram, the X on the trouble-shooting chart
1The first lap of 6 blades, in like manner X are measured in expression
2, X
3, X
4, X
5Represent the measurement of the 2nd, 3,4,5 circles that the blade rotor experiment table rotates respectively, each triangle symbol of figure upper bottom portion represents to segment the pulse that phase discrimination signal produces, other triangle symbol is represented the signal pulse that every blade pass produces when crossing blade pulse transducer probe, the numbering of corresponding 6 blades of the sequence number at figure top;
(5) COMPUTER CALCULATION X
IjValue equal 0, observe trouble-shooting chart, find out every blade on the trouble-shooting chart in each blade signal pulse that produces during by the blade pulse transducer and each self-corresponding segmentation phase discrimination signal pulse all on same straight line, blade does not have fault;
(6) click " stop sampling " button on the interface with left mouse button;
(7) click the Close button in the upper right corner, interface with left mouse button, withdraw from spacing monitoring, diagnosing software systems between turbomachine blade fault leaf;
(8) click " closing " option in the Start menu with left mouse button, shut down computer;
(9) cut off the electricity supply, impeller stops operating;
(10) take off first blade from impeller;
(11) repeated priming motor makes turbomachine turn to the process that blade signal pulse and phase discrimination signal pulse enter computing machine;
(12) show blade signal pulse figure, phase discrimination signal pulse diagram and trouble-shooting chart, there are two spacings between the blade pulse that obvious variation has taken place on the blade signal pulse figure of this moment, the complete obiteration of a blade signal pulse has been arranged, can initial analysis going out according to the pulse on the phase discrimination signal pulse diagram simultaneously is that first blade may fracture or break, observe trouble-shooting chart, the blade pulse complete obiteration of first blade, i.e. X
I1For infinity, judge that tentatively the number one blade fractures or break;
(13) COMPUTER CALCULATION X
IjValue, X
I1Value be infinitely great, computing machine sends chimes of doom;
(14) click " stop sampling " button on the interface with left mouse button;
(15) disable motor stops operating impeller;
(16) click the Close button in the upper right corner, interface with left mouse button, withdraw from spacing monitoring, diagnosing software between turbomachine blade fault leaf;
(17) click " closing " option in the Start menu with left mouse button, shut down computer.
3, spacing monitoring, diagnosing method between turbomachine blade fault leaf according to claim 1 is characterized in that the monitoring, diagnosing step of flexible blade is as follows:
(1) repeated priming motor makes turbomachine turn to the process of the input number of blade;
(2) click the button of " flexible blade " with left mouse button, enter spacing monitoring, diagnosing between the flexible blade leaf;
(3) the phase discrimination signal pulse of the blade signal pulse that collects of blade pulse transducer and phase demodulation sensor acquisition enters computing machine through filtering, the processing and amplifying of fore-lying device;
(4) trouble-shooting chart of 6 flexible blades of demonstration, the X on this trouble-shooting chart
1Represent the first lap that 6 flexible blades are measured, X is in like manner arranged
2, X
3, X
4, X
5Represent measurements respectively to the 2nd, 3,4,5 circles of whole turbomachine rotation, each triangle symbol of figure upper bottom portion represents to segment the pulse that phase discrimination signal produces, other triangle symbol is represented the pulse that every blade pass produces when crossing blade pulse transducer probe, the numbering of the corresponding blade of the sequence number at figure top;
(5) X of each blade correspondence of COMPUTER CALCULATION
IjMean value equal 0, observe the trouble-shooting chart of 6 flexible blades, though find out every blade on the trouble-shooting chart in each blade signal pulse that produces during by the blade pulse transducer and each self-corresponding segmentation phase discrimination signal pulse not on same straight line, but they are always paced up and down about each self-corresponding segmentation phase discrimination signal pulse position, their mean place and each self-corresponding segmentation phase discrimination signal pulse position are on same straight line, and blade does not have fault;
(6) repeat the step that " stopping sampling " stops operating to impeller;
(7) make No. three blade tip bending;
(8) the repeated priming motor enters the step of computing machine to blade signal pulse and phase discrimination signal pulse;
(9) show trouble-shooting chart, observe trouble-shooting chart, find out that No. three blades on the trouble-shooting chart compare hysteresis in the mean place segmentation phase discrimination signal pulse position corresponding with it of each blade signal pulse that produces during by blade sensor, No. three blade has bending blade;
(10) X of each blade correspondence of COMPUTER CALCULATION
IjMean value, wherein, the X of No. three blade
I3Mean value greater than 0, computing machine sends chimes of doom;
(11) repeat " stopping sampling " to the step of shutting down computer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB021133735A CN1150400C (en) | 2002-02-09 | 2002-02-09 | Monitoring and diagnosing method for the gap between defective vanes of vane machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB021133735A CN1150400C (en) | 2002-02-09 | 2002-02-09 | Monitoring and diagnosing method for the gap between defective vanes of vane machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1364998A true CN1364998A (en) | 2002-08-21 |
| CN1150400C CN1150400C (en) | 2004-05-19 |
Family
ID=4742581
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB021133735A Expired - Fee Related CN1150400C (en) | 2002-02-09 | 2002-02-09 | Monitoring and diagnosing method for the gap between defective vanes of vane machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1150400C (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100511308C (en) * | 2004-06-28 | 2009-07-08 | Abb研究有限公司 | System and method for inhibiting redundant warning |
| CN101360980B (en) * | 2006-02-03 | 2010-07-28 | 阿利发Np有限公司 | Method and device for detecting the position of a pulsed mechanical effect on a plant component |
| CN101986539A (en) * | 2009-06-16 | 2011-03-16 | 武汉市创佳源电子有限公司 | Mechanical structures of efficient linear power supply module and input/output interface method |
| CN101592590B (en) * | 2008-05-26 | 2013-06-19 | 唐德尧 | Fault indirect diagnosis technique of rotating blade |
| CN105371792A (en) * | 2014-08-25 | 2016-03-02 | 广西南宁西格汇居电子科技有限公司 | Turning axis digital phase distinguishing measurement method |
| CN106247893A (en) * | 2016-08-25 | 2016-12-21 | 中航动力股份有限公司 | A kind of string width measuring tool of high-pressure turbine guide vane |
| CN108267504A (en) * | 2016-12-30 | 2018-07-10 | 爱德森（厦门）电子有限公司 | A kind of ferromagnetism motor body intra vane dynamic in-situ monitoring method |
| CN109579665A (en) * | 2018-12-24 | 2019-04-05 | 上海起帆电缆股份有限公司 | Metal tape armour gap measuring method |
| CN116558840A (en) * | 2023-07-12 | 2023-08-08 | 唐智科技湖南发展有限公司 | Method, device, equipment and storage medium for monitoring aero-engine blade |
-
2002
- 2002-02-09 CN CNB021133735A patent/CN1150400C/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100511308C (en) * | 2004-06-28 | 2009-07-08 | Abb研究有限公司 | System and method for inhibiting redundant warning |
| CN101360980B (en) * | 2006-02-03 | 2010-07-28 | 阿利发Np有限公司 | Method and device for detecting the position of a pulsed mechanical effect on a plant component |
| CN101592590B (en) * | 2008-05-26 | 2013-06-19 | 唐德尧 | Fault indirect diagnosis technique of rotating blade |
| CN101986539A (en) * | 2009-06-16 | 2011-03-16 | 武汉市创佳源电子有限公司 | Mechanical structures of efficient linear power supply module and input/output interface method |
| CN105371792A (en) * | 2014-08-25 | 2016-03-02 | 广西南宁西格汇居电子科技有限公司 | Turning axis digital phase distinguishing measurement method |
| CN106247893A (en) * | 2016-08-25 | 2016-12-21 | 中航动力股份有限公司 | A kind of string width measuring tool of high-pressure turbine guide vane |
| CN106247893B (en) * | 2016-08-25 | 2019-04-02 | 中航动力股份有限公司 | A kind of chord width measuring tool of guide vane of high pressure turbine |
| CN108267504A (en) * | 2016-12-30 | 2018-07-10 | 爱德森（厦门）电子有限公司 | A kind of ferromagnetism motor body intra vane dynamic in-situ monitoring method |
| CN108267504B (en) * | 2016-12-30 | 2021-08-24 | 爱德森（厦门）电子有限公司 | Dynamic in-situ monitoring method for blades in ferromagnetic engine shell |
| CN109579665A (en) * | 2018-12-24 | 2019-04-05 | 上海起帆电缆股份有限公司 | Metal tape armour gap measuring method |
| CN116558840A (en) * | 2023-07-12 | 2023-08-08 | 唐智科技湖南发展有限公司 | Method, device, equipment and storage medium for monitoring aero-engine blade |
| CN116558840B (en) * | 2023-07-12 | 2023-10-13 | 唐智科技湖南发展有限公司 | Method, device, equipment and storage medium for monitoring aero-engine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1150400C (en) | 2004-05-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101592590B (en) | Fault indirect diagnosis technique of rotating blade | |
| CN101435799B (en) | Failure diagnosis method and apparatus of hydroturbine based on acoustic emission technology | |
| CN109488630B (en) | Centrifugal fan rotor misalignment fault diagnosis method based on harmonic relative index | |
| CN103323274B (en) | Condition monitoring for rotating machinery and fault diagnosis system and method | |
| JP2824523B2 (en) | Method and apparatus for measuring fatigue of vibrating member | |
| CN111963415A (en) | Fault diagnosis method and system for hydraulic plunger pump | |
| CN111397877B (en) | Rotary machine beat vibration fault detection and diagnosis method | |
| CN108956075A (en) | Movable vane piece crackle inline diagnosis method | |
| CN1150400C (en) | Monitoring and diagnosing method for the gap between defective vanes of vane machine | |
| CN113092113B (en) | Rolling bearing fault diagnosis system based on spectral value ratio | |
| CN110686764A (en) | Method for measuring asynchronous vibration frequency of constant-speed blade based on full-phase difference principle | |
| EP0463108A1 (en) | Shaft crack detection method | |
| Krause et al. | Asynchronous response analysis of non-contact vibration measurements on compressor rotor blades | |
| EP1793226A2 (en) | Methods and systems for ultrasound inspection | |
| Fan et al. | Shifting straight-line fitting method to calculate blade vibration based on blade tip timing | |
| Wu et al. | Blade crack detection using blade tip timing | |
| JP6185541B2 (en) | Wind turbine blade inspection method | |
| CN112417622A (en) | Method and system for evaluating mechanical vibration of unit, computer equipment and storage medium | |
| Junior et al. | Unbalance evaluation of a scaled wind turbine under different rotational regimes via detrended fluctuation analysis of vibration signals combined with pattern recognition techniques | |
| CN103335842A (en) | Bearing fault recognition system based on probability density curve and method thereof | |
| Sahoo et al. | Health monitoring of wind turbine blades through vibration signal using advanced signal processing techniques | |
| Al-Hadad et al. | Vibration characteristic responses due to transient mass loading on wind turbine blades | |
| CN111562126B (en) | Rotary mechanical frequency doubling fault diagnosis method based on three-dimensional holographic difference spectrum | |
| JPH05296888A (en) | Diagnostic apparatus for rotary machine | |
| CN111766299A (en) | Steam turbine blade crack assessment system and steam turbine blade crack early warning method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C06 | Publication | ||
| PB01 | Publication | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |