CN1067765C - Rotor holographic dynamic balance method - Google Patents
Rotor holographic dynamic balance method Download PDFInfo
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Abstract
The present invention relates to a rotor holographic dynamic balance method which belongs to the field of rotary mechanical vibration diagnosis and control. Based on the principle of holographic spectrum information integration, the information of amplitude, frequencies and phases is integrated so as to comprehensively describe the vibration behavior of the rotors on the basis of obtaining all the sensor vibration information of rotors; the vibration behavior can be used as reference for evaluating the unbalance state of the rotors and trial mass influence so as to select an optimum balance plane of the rotors, weighting mass and orientation.
Description
The invention belongs to the rotor dynamic balancing technical field, further relate to rotating machinery vibrating diagnosis and control field.
At present, the rotor dynamic balancing method is distinguished from principle, can be classified as two big class, i.e. method of model balancing and influence coefficient methods.Method of model balancing need be to the vibration shape of rotor-support-foundation system, and parameters such as critical rotary speed have the understanding of priori, and these parameters are too many and approximate owing to hypothesis when calculating, and influences the precision and the efficient of balance.Influence coefficient method need repeatedly increase the weight of to measure the influence coefficient matrix of reflection rotor unbalance response overall picture, in addition, and owing to balanced surface is selected reason such as improper and is easily impacted matrix of coefficients morbid stateization.Thereby present two kinds of balance methods all need a large amount of artificial participations, rely on balance expert's experience too much.Process is gathered in the manual examination of the balance of flexible rotor still a kind of basically (under theory instructs).
On the other hand, the vibration signal that present balance is utilized all is from unidirectional collection with a sensor.Do like this being based on rotor-support-foundation system each to hypothesis of equal stiffness, rotor each when there is notable difference in rigidity, existing method will inevitably be brought error, reduces balance quality, has a strong impact on the efficient of balance.
The object of the present invention is to provide a kind of brand-new, intuitive, clear dynamic balance method.This method is based on the integrated principle of holographic spectrum information, on the basis that obtains all sensors vibration information on the rotor, the integrated width of cloth, frequently, phase information, to describe the vibration behavior of rotor all sidedly, as the foundation of evaluation rotor imbalance state and test mass influence, thereby select rotor optimum balance face and increase the weight of quality and orientation.
Concrete implementation step of the present invention following (the present invention can be used for spot dynamic balance, also can be used for the transformation of existing equilibrator because the principle of these two kinds of methods is the same, the implementation step when setting forth field balancing emphatically here.)：
1. gather fault unit data, utilize holographic spectrum can correctly distinguish the character of fault, distinguish whether unit takes fault as the leading factor with imbalance.If then carry out next step.
2. according to the situation of on-the-spot machine group rotor, decision increases the weight of the face number.
3. the data of gathering are carried out the data pre-service, with key signal normalization.
4. utilize holographic spectrum software, accurately obtain amplitude, frequency and the phase place of the signal that each sensor picks up.Make two-dimension holographic spectrum of each data acquisition face and the 3D hologram spectrum under the rotor commentaries on classics frequently.
5. three-dimensional is changeed holographic spectral factorization frequently, relatively the size of force unbalance and couple unbalance first phase point vector determines balance scheme according to result relatively.Scheme mainly comprises preferential balance static unbalance, and preferential equilibrant couple unbalance and power, couple be balance simultaneously.Three kinds of schemes corresponding respectively three kinds of comparative results.
6. according to balance scheme,, determine size and orientation that test mass adds in conjunction with the balancing speed of unit.For be operated in one, rotor between the second order critical rotary speed, its static(al) component is oppositely synthesized a vector with the couple component in the back again, increase the weight of in the opposite direction of this vector.
With the method for interpolation test mass of the present invention, for two plane of unbalances, the rotor of two counterweight faces can just can obtain effect preferably when adding test mass for the first time, thereby reduces the cycling start number of times, improves balance efficiency.
7. gather the data after increasing the weight of, make the test mass track.
8. the test mass track is decomposed, whether the static(al) after check is decomposed, the first phase point of couple component drop within the corresponding phase shift ellipse, according to itself and the differential seat angle of phase shift elliptical center and the ratio of size, determine size and the angle that static(al), couple component should be revised respectively.With the static(al) component is that example illustrates, with reference to Fig. 1.
Among Fig. 1,1 is the phase shift ellipse, and 2 is the static(al) component of test mass track, and 3 is the static(al) component of initial trace, and 4 is the first phase point.Initial trace static(al) component first phase point is P
O, the static(al) component first phase point of test mass track is A.Effective balance test mass, its test mass track first phase point should drop within the phase shift ellipse of initial trace.And should be with the center of circle of phase shift ellipse for making great efforts target.So the static(al) component of test mass should make the oval first phase point B that forms of test mass be in the circle center line connecting OO of original ellipse and phase shift ellipse
1On.Then this static(al) component should be along moving past the AOB angle on the circumference, and the first phase point that makes formation is over against P
O
The correction of static(al) component is than the ratio of the first phase point radius vector that should equal original ellipse and test mass ellipse.That is to say OP
ORatio with OB.
9. two added test mass in plane are decomposed into force unbalance amount and couple unbalance amount.According to definite static(al) of the 8th step, the correction of couple component, revise force unbalance amount and couple unbalance amount respectively.
The corrected force unbalance amount and the couple unbalance amount vector on two planes is synthetic 10..Result after synthetic promptly be two planes the corrective weight that should add.
After 11. corrective weight adds, the result after test increases the weight of once more, if satisfy the balance requirement, then balance finishes.Otherwise, repeated for the 3rd～10 step.
Holographic dynamic balance method provided by the invention has been opened up new thinking for dynamic balance field, has shown following superiority:
1. utilized the information of bilateral transducer fully, considered that rotor-bearing system both direction rigidity does not wait the influence to data.Compose parameter with holography, wait the intensity that characterizes vibration as semi-major axis, first phase point vector, also truer more comprehensively.
2. utilize graphics mode to show equilibrium process, result and effect, balance method is simple and clear.
3. the dependence to personnel's experience is low.When the present invention was used for spot dynamic balance, a large amount of calculating and angle judgement were finished on the backstage by software.Can reduce artificial judgement on the one hand and make mistakes, the technician of factory just can grasp by simple study on the other hand, makes the equipment control of factory that bigger independence be arranged.
4. the present invention utilizes the method for 3D hologram spectral factorization, and equilibrium problem is simplified.And by synthesizing once more after decomposing, make and once increase the weight of just can play effect preferably, improved the efficient of balance widely.
5. can realize that two planes increase the weight of simultaneously, reduce and opened the train number number.
The present invention repeatedly carried out checking on the rotor experiment table of production scene unit and this institute.Experiment table arranges that 1,2,3,4,5 are respectively five eddy current sensors among Fig. 2 as Fig. 2, and 6,7 are respectively plane one and plane two.
Rotor-support-foundation system increases the weight of dish by two and forms.Divide near two groups of vibrations the measurement bearings at both ends by four eddy current sensors respectively, an eddy current sensor is used for phase reference and measures.It is rotor (one, second order critical rotary speed between) when working speed 5600rpm that balance requires, and reduces original vibration and pass through first critical speed smoothly when starting.Whole experiment is as follows:
1 starts rotor to testing rotating speed, measures the original vibration of rotor under each rotating speed.Fig. 3 is the 3D hologram spectrum of rotor under 5600rpm.
For the needs of testing, we can add test mass, increase artificially uneven, and with the vibration after increasing the weight of as original vibration.
2 stop, and increase the weight of 0.75g respectively on the left and right dish of rotor, increase the weight of orientation such as Fig. 4, and (a) is plane one among Fig. 4, (b) is plane two.
3 start rotor once more to testing rotating speed, measure the vibration of rotor under each rotating speed.
With reference to Fig. 5, among Fig. 5 (a), (b) be respectively the two-dimension holographic spectrum on plane one and plane two.By Fig. 5, we know this moment rotor mainly based on imbalance fault, thereby we can carry out next step.And with this moment vibration as original vibration.4. data pre-service:
With reference to Fig. 6, (a) is the signal before handling among Fig. 6, (b) is the signal after handling.5. make the three-dimensional of rotor-support-foundation system and change holographic frequently spectrum:
When rotor speed is 5600RPM, experimental result that records such as back subordinate list.
After the holographic conversion, the holography spectrum parameter-holographic spectrogram first phase point that characterizes plane vibration is respectively: V1=42.18@-55.54 (plane one), V2=76.67@12.97 (plane two) is with reference to Fig. 7.6. three-dimensional is changeed holographic spectral factorization frequently:
(a) is the static(al) component after decomposing among Fig. 8, (b) is the couple component after decomposing.7. formulation balance scheme:
As shown in Figure 8, couple unbalance and static unbalance are all very important on the rotor.Thereby, relatively the safe course is and proofread and correct two kinds of imbalances simultaneously.8. add test mass:
Balancing speed is one, between the second order critical rotary speed, and oppositely the synthetic vector of back and couple component is reverse should to be added in the static(al) component when adding test mass.
Plane one, we oppositely synthesize the vector that obtains with the couple component with the static(al) component and are
U1′=76.67mv@-167.03；
Plane two, we oppositely synthesize the vector that obtains with the couple component with the static(al) component and are
U2′=42.18mv@124.46。
We should be at U1 ', and U2 ' oppositely increases the weight of.That is to say plane one 12.97 the degree increase the weight of.Increase the weight of at-55.54 degree on plane two.And the ratio of plane one and the size of test mass that plane two adds is 1.8.Owing to increase the weight of the restriction of screwhole position on the rotating disk circumference, the final size that adds test mass is 0.5g, and the orientation is respectively 22.5 degree and-37.5 degree, as shown in Figure 9, among Fig. 9 (a), (b) is respectively plane one, plane two.9. measure the vibration after increasing the weight of:
As what we expected, owing to the accuracy that increases the weight of on the orientation general orientation, vibration has obtained inhibition to a certain extent.As shown in figure 10.
Make the test mass track as shown in figure 11.
The test mass track characterizes the influence of test mass based on static(al), and the character that this also is with we increase the weight of is consistent.Further and since the main balance of test mass the static unbalance component of rotor-support-foundation system, Figure 11 characterizes rotor-support-foundation system this moment based on couple unbalance.The test mass track is decomposed as Figure 12 13.
Figure 12, among Figure 13, dotted line is depicted as the phase shift ellipse, and solid line is respectively the decomposition result of initial trace and test mass track.Among Figure 12, the first phase point of test mass track static(al) component just is positioned at the opposite direction position of initial trace static(al) component first phase point, that is to say the phase shift elliptical center position of initial trace static(al) component, thereby the most static unbalance of rotor is offset.Compare Figure 12 respectively, Figure 13 pilot scale heavy rail mark first phase point vector and phase shift elliptical center position, we are not difficult to draw following correction:
The static(al) component: size increases 1.07 times, and angle is rotated counterclockwise 2.2 degree;
The couple component: size increases 2.57 times, angle 31.4 degree that turn clockwise.10. correction test mass:
Simultaneously, we also are decomposed into static unbalance amount and couple unbalance amount with the unbalance dynamic test mass that adds.As shown in figure 14.
F
1Be the static unbalance component of plane one with plane two.C
1And C
2Be respectively the couple unbalance component on plane one, two.Suppose accordingly that based on system linear the static(al) of test mass track, couple component can be regarded as by F
1, F
1And C
1, C
2Produce.By the conclusion in the 9th step, according to the principle of linear effect, F
1Correction result F
1' should equal:
F
1′=F
1*1.07@2.2=0.46g@-5.3
In like manner, C
1, C
2Correction result C
1' C
2' should equal:
C
1′=C
1*2.57@-31.4=0.64g@51.1
C
2′=C
2*2,57@-31.4=0.64g@-128.9
The counterweight on final plane one should equal F
1' and C
1' synthetic:
S
1=0.46g@(-5.3)+0.64g@51.1=0.97g27.9
The counterweight on plane two should equal F
1' and C
2' synthetic:
S
2=0.46g@(-5.3)+0.64g@(-128.9)=0.54g-84.07
S
1And S
2Vector roughly be positioned at amount of unbalance U1 that we added and U2 oppositely, and its size is more or less the same with U1, U2, well imagines that we are at S
1And S
2Vector position increases the weight of and will play effect preferably.
S
1And S
2Be on the basis of not considering the amount of unbalance influence that original rotor-support-foundation system exists, to calculate.If we consider to go up the initial unbalance of original rotor-support-foundation system, they are rejected the S as a result that calculates from test figure
1' and S
2' will be more near U1, U2 oppositely.Specific practice is that the vibration vector that the back records is each time deducted the initial vibration vector that the 1st pacing gets.Computation process here no longer is described in detail, the S as a result that calculates
1' and S
2' be:
S
1′=0.90g@28
S
2′=0.84g@-107
S
1, S
2And S
1', S
2' orientation such as Figure 15:
We are as follows with the data list of whole test at last:
All vibration vectors are the holography spectrum parameter-holography spectrum first phase point vector of holographic conversion.
The mv@ of table one unit degree
| Plane one | Plane two | |
| 1. the rotor oscillation that does not increase the weight of | 32.14@32.73 | 13.51@22.0 |
| 2. the uneven counterweight that adds | 0.7g@202.5 | 0.7g@67.5 |
| 3. original vibration | 42.18@-55.54 | 76.67@12.97 |
| 4. the test mass vector that adds | 0.5g@22.5 | 0.5g@-37.5 |
| 5. add the vibration behind the test mass | 24.02@-142.55 | 27.22@21.06 |
| 6. test mass track | 47.44@154.84 | 49.87@-171.43 |
| 7. test mass decomposes (static(al)) (couple) | 0.43g@-7.5 0.25g@82.5 | 0.43g@-7.5 0.25g@-97.5 |
| 8. (static(al)) (couple) decomposed in original vibration | 50.1@-10.1 36.36@-134.36 | 50.1@-10.1 36.36@45.64 |
| 9. the test mass track decomposes (static(al)) | 46.56@172.14 | 46.56@172.14 |
| (couple) | 14.14@77 | 14.14@103 |
| 8. with 9. after relatively: the static(al) component of test mass should increase 1.07 times, be rotated counterclockwise 2.2 degree simultaneously.The couple component of test mass should increase 2.57 times, and 31.4 degree simultaneously turn clockwise. | ||
| 10. test mass static(al) component correction result | 0.46g@-5.3 | 0.46g@-5.3 |
| 11. test mass couple component correction result | 0.64g@51.1 | 0.64g@-128.9 |
| 12. final counterweight (correction result is synthetic) | 0.97g@27.9 | 0.54g@-84.07 |
| Above result obtains under the situation of 1. influence not considering, if we reject the unbalanced influence of rotor itself, resulting result is: | ||
| 13. original vibration | 52.25@-93.48 | 63.36@11.05 |
| 14. add the vibration behind the test mass | 56.11@-145.25 | 13.71@20.13 |
| 15. test mass track | 47.44@154.84 | 49.87@-171.43 |
| 16. the test mass track decomposes (static(al)) (couple) | 46.56@172.14 14.14@77 | 46.56@172.14 14.14@103 |
| 17. (static(al)) (couple) decomposed in original vibration | 35.65@-34.13 45.84@-135.46 | 35.65@-34.13 45.84@44.54 |
| 18. revised counterweight result | 0.90g@28 | 0.84g@-107 |
| Result of calculation and added amount of unbalance are approaching more as can be seen. | ||
| 19.18 the result add later remaining amount of unbalance | 0.22g@47.75 | 0.21g@-88.73 |
| Remaining amount of unbalance is 30% of an original unbalance. | ||
In order to compare, we also can adopt directions X signal or Y direction signal to calculate separately, and its comparative result sees Table two.Table two mv@ degree
| Balance method | Use the directions X signal separately | Use the Y direction signal separately | Holographic dynamic balance method | |||
| The plane | Plane one | Plane two | Plane one | Plane two | Plane one | Plane two |
| Original vibration | 39.93@-5.56 | 52.18@-89.17 | 63.59@101.06 | 55.57@11.63 | 52.25@-93.48 | 63.36@11.05 |
| Vibration after increasing the weight of | 52.11@-63.24 | 62.93@-150.45 | 13.06@98.28 | 6.57@44.88 | 56.11@-145.25 | 13.71@20.13 |
| Influence vector | 45.66@-110.89 | 50.55@-78.22 | 59.39@159.15 | 50.20@-172.48 | 47.44@154.84 | 49.87@-171.43 |
| Result of calculation | 1.06g@40.78 | 0.48g@-234.32 | 0.87@14.03 | 0.67@-127.75 | 0.90g@28 | 0.84g@-107 |
| Angular error | 18.28 | -13.18 | -8.47 | -15.25 | 5.5 | 5.5 |
Can find out that from result of calculation with the result that holographic dynamic balance method calculates, its precision is apparently higher than method from folk prescription to signal that use.And quite big with directions X calculated signals time error, though also can obtain the result that comparatively is satisfied with when calculating with the Y direction signal, this can't know in the past in balance.Thereby existing most of ways are the on-site experiences by means of the expert, after choosing a direction, add an offset angle artificially, to remedy the error that the rotor anisotropy is brought.Holographic dynamic balance then need not be considered this point, thereby can improve balance quality, and progressively breaks away from the dependence to the balance expert.
Claims (3)
1. rotor holographic dynamic balance method, at first gather fault unit data, distinguish whether unit takes fault as the leading factor with imbalance, if, then according to the situation of fault machine group rotor, decision increases the weight of the face number, and the data of gathering are carried out the data pre-service, with key signal normalization, feature of the present invention is, adopt holographic spectrum can distinguish whether unit takes fault as the leading factor with imbalance, and:
(1) utilize holographic spectrum software, accurately obtain amplitude, frequency and the phase place of the signal that each sensor picks up, the 3D hologram that making the two-dimension holographic spectrum of each data acquisition face and rotor changes is frequently down composed;
(2) three-dimensional is changeed holographic spectral factorization frequently, relatively the size of force unbalance and couple unbalance first phase point vector determines balance scheme according to result relatively;
(3),, determine size and orientation that test mass adds in conjunction with the balancing speed of unit according to balance scheme;
(4) data after collection increases the weight of are made the test mass track;
(5) the test mass track is decomposed, whether the static(al) after check is decomposed, the first phase point of couple component drop within the corresponding phase shift ellipse, according to itself and the differential seat angle of phase shift elliptical center and the ratio of size, determine size and the angle that static(al), couple component should be revised respectively;
(6) two added test mass in plane are decomposed into force unbalance amount and couple unbalance amount,, revise force unbalance amount and couple unbalance amount respectively according to definite static(al) of (5) step, the correction of couple component;
(7) the corrected force unbalance amount on two planes and couple unbalance amount vector is synthetic, the result after synthetic promptly be two planes the corrective weight that should add;
(8) after corrective weight adds, the result after test increases the weight of once more, if satisfy the balance requirement, then balance finishes; Otherwise, repeat above-mentioned steps.
2. rotor holographic dynamic balance method according to claim 1 is characterized in that, said balance scheme comprises preferential balance static unbalance, and preferential equilibrant couple unbalance and power, couple be balance simultaneously.
3. rotor holographic dynamic balance method according to claim 1 is characterized in that, for be operated in one, rotor between the second order critical rotary speed, with its static(al) component oppositely and the couple component synthesize a vector again, increase the weight of in the opposite direction of this vector.
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| CN100434890C (en) * | 2005-12-12 | 2008-11-19 | 西安交通大学 | Flexible rotor holographic dynamic balancing method based on empirical mode decomposition |
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