CN114061729A - Rotor sudden-change vibration fault positioning method and system - Google Patents

Rotor sudden-change vibration fault positioning method and system Download PDF

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Publication number
CN114061729A
CN114061729A CN202111232415.8A CN202111232415A CN114061729A CN 114061729 A CN114061729 A CN 114061729A CN 202111232415 A CN202111232415 A CN 202111232415A CN 114061729 A CN114061729 A CN 114061729A
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Prior art keywords
vibration
rotor
fault
beta
alpha
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Inventor
邓中乙
陈悦
吴仲
张辉
李建华
刘海东
章正林
阮圣奇
陈胜利
肖宇煊
庞靖
邢海波
李敬豪
袁昊
邵飞
司翔宇
宋勇
朱涛
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Datang Boiler Pressure Vessel Examination Center Co Ltd
East China Electric Power Test Institute of China Datang Corp Science and Technology Research Institute Co Ltd
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Datang Boiler Pressure Vessel Examination Center Co Ltd
East China Electric Power Test Institute of China Datang Corp Science and Technology Research Institute Co Ltd
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Priority to CN202111232415.8A priority Critical patent/CN114061729A/en
Publication of CN114061729A publication Critical patent/CN114061729A/en
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
    • G01H1/00—Measuring characteristics of vibrations in solids by using direct conduction to the detector
    • G01H1/003—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines
    • G01H1/006—Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines of the rotor of turbo machines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M13/00—Testing of machine parts
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines

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  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)

Abstract

The invention discloses a method and a system for positioning sudden change vibration fault of a rotor, which comprises the following steps: step 1, recording vibration vectors before sudden change of vibration at two ends of a rotor in the same direction
Figure DDA0003316358310000011
And
Figure DDA0003316358310000012
abrupt change of vibration vector
Figure DDA0003316358310000013
And
Figure DDA0003316358310000014
step 2, calculating vibration variation
Figure DDA0003316358310000015
Step 3, the vibration variation quantity is adjusted
Figure DDA0003316358310000016
And
Figure DDA0003316358310000017
harmonic component decomposition
Figure DDA0003316358310000018
Wherein
Figure DDA0003316358310000019
The phase angle of (a) is alpha,
Figure DDA00033163583100000110
has a phase angle of beta; step 4, if alpha-beta is approximately equal to 90 degrees or alpha-beta is approximately equal to-90 degrees, the vibration fault point is close to the side A; if it is
Figure DDA00033163583100000111
If the value is far greater than 1, the vibration variable is mainly the same direction component, and the corresponding fault point is located in the middle of the rotor. The invention adopts the harmonic component decomposition of the vibration variation before and after the rotor fault, thereby obtaining
Figure DDA00033163583100000112
The phase angle of (a) is alpha,
Figure DDA00033163583100000113
the phase angle is beta, and the fault point is judged according to the phase angle, so that the whole calculation process is simple and the positioning is accurate.

Description

Rotor sudden-change vibration fault positioning method and system
Technical Field
The invention relates to the technical field of mechanical vibration fault analysis of a steam turbine, in particular to a method and a system for positioning sudden-change vibration fault of a rotor.
Background
When the steam turbine takes place the vibration trouble, often can lead to some harmful results to produce, make the normal operation of steam turbine and production receive great influence, can lead to the steam turbine overall to take place the condition of destroying even. When some vibration faults occur in the unit, not only the nature of the fault needs to be judged, but also the fault point is located at the axial and circumferential positions of the rotor.
For diagnosis and positioning of some sudden-change vibrations, the method can not only provide auxiliary criteria for judging the nature of the fault, but also guide the direction of unit maintenance and avoid meaningless expansion of the maintenance range for positioning hidden faults such as turn-to-turn short circuit of the generator rotor. The prior art can detect that the rotor has faults and can not accurately judge fault points. The wavelet-gray level co-occurrence matrix-based engine rotor collision and abrasion fault diagnosis method disclosed in application number 202110668493.6 solves the problems of low fault identification precision, high requirements of a neural network method on samples and hardware and tedious training of the traditional method. The method comprises the following specific steps: 1) collecting engine friction data; 2) performing wavelet transformation on the engine rub-impact data to obtain a vibration signal wavelet transformation diagram; 3) converting the wavelet transform map of the vibration signal into a gray scale map, extracting the gray scale co-occurrence matrix image characteristic quantity of the gray scale map, and constructing a characteristic vector; 4) setting labels for the feature vectors, and dividing the feature vectors into a training set and a test set; 5) inputting the training set into a machine learning algorithm support vector machine for training to obtain a trained support vector machine; 6) and inputting the test set into a trained support vector machine to realize the collision and abrasion fault diagnosis of the engine rotor. Although this method can solve the problem of failure diagnosis, it cannot locate the failure position.
Disclosure of Invention
The invention aims to solve the technical problem of how to quickly locate the fault position of the rotor.
The invention solves the technical problems through the following technical means:
the method for positioning the sudden change vibration fault of the rotor comprises the steps that the symmetrical rotor comprises the rotor, a plurality of level blades symmetrically fixed on the rotor and supporting points A, B; the support points A, B respectively provide support for two ends of the rotor; assuming that a certain level of blade falls off, the method for judging the position of the fault point comprises the following steps:
step 1, recording two ends of the rotor to be the sameVibration vector before sudden change of vibration in one direction
Figure BDA0003316358290000011
And
Figure BDA0003316358290000012
abrupt change of vibration vector
Figure BDA0003316358290000013
And
Figure BDA0003316358290000014
step 2, calculating vibration variation
Figure BDA0003316358290000015
Step 3, the vibration variation quantity is adjusted
Figure BDA0003316358290000021
And
Figure BDA0003316358290000022
harmonic component decomposition
Figure BDA0003316358290000023
Wherein
Figure BDA0003316358290000024
The phase angle of (a) is alpha,
Figure BDA0003316358290000025
has a phase angle of beta;
step 4, if alpha-beta is approximately equal to 90 degrees or alpha-beta is approximately equal to-90 degrees, the vibration fault point is close to the side A; if it is
Figure BDA0003316358290000026
If the value is far greater than 1, the vibration variable is mainly the same direction component, and the corresponding fault point is located in the middle of the rotor.
The invention carries out harmonic component on the vibration variation before and after the rotor faultIs decomposed to obtain
Figure BDA0003316358290000027
The phase angle of (a) is alpha,
Figure BDA0003316358290000028
the phase angle is beta, and the fault point is judged according to the phase angle, so that the whole calculation process is simple and the positioning is accurate.
Further, the vibration in the other direction on the same rotor is calculated and judged according to the steps 1 to 4.
Further, in the step 4, when the angle α - β ≈ 90 °, the fault position is
Figure BDA0003316358290000029
Wherein the distance between the falling point and the A side weighted plane is LaThe axial distance of the weighted planes on both sides of the supporting point A, B is L,
Figure BDA00033163582900000210
for the co-directional component influence coefficient,
Figure BDA00033163582900000211
is an inverse component influence coefficient.
Further, in the step 4, when the angle alpha-beta is approximately equal to-90 degrees, the fault position is
Figure BDA00033163582900000212
Corresponding to the method, the invention also provides a rotor sudden-change vibration fault positioning system, wherein a symmetrical rotor comprises a rotor, a plurality of level blades symmetrically fixed on the rotor, and supporting points A, B; the support points A, B respectively provide support for two ends of the rotor; assuming that a blade of a certain level is detached, the system for determining the position of the fault point includes:
the rotor sudden change front and back vibration vector recording module is used for recording the vibration vectors of the two ends of the rotor before sudden change in the same direction
Figure BDA00033163582900000213
And
Figure BDA00033163582900000214
abrupt change of vibration vector
Figure BDA00033163582900000215
And
Figure BDA00033163582900000216
a vibration variation calculating module for calculating vibration variation
Figure BDA00033163582900000217
Harmonic component decomposition module for the vibration variation
Figure BDA00033163582900000218
And
Figure BDA00033163582900000219
harmonic component decomposition
Figure BDA00033163582900000220
Figure BDA00033163582900000221
Wherein
Figure BDA00033163582900000222
The phase angle of (a) is alpha,
Figure BDA00033163582900000223
has a phase angle of beta;
if alpha-beta is approximately equal to 90 degrees or alpha-beta is approximately equal to-90 degrees, the fault point judgment module indicates that the vibration fault point is close to the side A; if it is
Figure BDA0003316358290000031
If the vibration variable is far more than 1, the vibration variable is mainly the same direction component, and the corresponding fault point is positioned in the middle part of the rotor。
Further, the vibration in the other direction on the same rotor is calculated and judged according to the steps 1 to 4.
Further, in the fault point judgment module, when the angle alpha-beta is approximately equal to 90 degrees, the fault position is
Figure BDA0003316358290000032
Wherein the distance between the falling point and the A side weighted plane is LaThe axial distance of the weighted planes on both sides of the supporting point A, B is L,
Figure BDA0003316358290000033
for the co-directional component influence coefficient,
Figure BDA0003316358290000034
is an inverse component influence coefficient.
Furthermore, in the fault point judgment module, when the angle alpha-beta is approximately equal to-90 degrees, the fault position is
Figure BDA0003316358290000035
The invention has the advantages that:
the invention belongs to a rotor vibration fault diagnosis and fault location method, which is suitable for rotary equipment provided with an online vibration monitoring system
Figure BDA0003316358290000036
The phase angle of (a) is alpha,
Figure BDA0003316358290000037
the phase angle is beta, the relative position of a fault point in the axial direction is judged according to the phase angle, the whole calculation process is simple, the structural fault is accurately positioned, and the position of a component with the fault of the rotor can be accurately judged by combining the structural characteristics of rotors of different devices.
Drawings
FIG. 1 is a schematic structural diagram of a symmetrical rotor applied to a method for locating a sudden rotor vibration fault in an embodiment of the present invention;
fig. 2 is a flow chart of a rotor sudden-change vibration fault locating method in the embodiment of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the embodiments of the present invention, and it is obvious that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment provides a method for positioning sudden change vibration fault of a rotor, as shown in fig. 1, wherein fig. 1 is a schematic structural diagram of a symmetrical rotor, and the symmetrical rotor comprises a rotor, blades and supporting bearing bushes a and B. For such a rotor and supporting point A, B system, the rotor has mechanism failure (e.g. some stage of blade has part falling off, the falling mass is m, the distance from the falling point to the A side weighted plane is LaA, B, the axial distance of the weighted planes on both sides is L), vibration changes, and as shown in FIG. 2, the method for determining the position of the fault point mainly comprises the following steps:
step 1, recording vibration vectors of two ends of a rotor in the same direction (X direction or Y direction) before sudden change of vibration
Figure BDA0003316358290000041
And
Figure BDA0003316358290000042
abrupt change of vibration vector
Figure BDA0003316358290000043
And
Figure BDA0003316358290000044
step 2, calculating vibration variation
Figure BDA0003316358290000045
Step 3, the vibration variation quantity is adjusted
Figure BDA0003316358290000046
And
Figure BDA0003316358290000047
harmonic component decomposition
Figure BDA0003316358290000048
Wherein
Figure BDA0003316358290000049
The phase angle of (a) is alpha,
Figure BDA00033163582900000410
has a phase angle of beta;
as shown in FIG. 1, the mass m causes an additional centrifugal force F in the direction opposite to the drop-off position, which force F is equivalent to that at the weight plane a according to the force translation principle
Figure BDA00033163582900000411
And couple FLaIt can be considered that there are forces in the same magnitude and opposite directions in the plane b
Figure BDA00033163582900000412
Thus, in-phase component force is formed in the planes a and b
Figure BDA00033163582900000413
And couple of opposite phase components
Figure BDA00033163582900000414
(couple FLa with
Figure BDA00033163582900000415
In the opposite direction).
According to the harmonic component method, the rotor vibration at the working rotation speed is decomposed into in-phase (symmetrical) component vibration and anti-phase (anti-symmetrical) component vibration, the in-phase component is caused by first-order unbalance of the rotor, the anti-phase component vibration is caused by second-order unbalance (couple unbalance) of the rotor and accords with the orthogonal relation, and therefore in-phase weighting mass and anti-phase weighting mass are obtained.
Equidirectionally weighted mass
Figure BDA00033163582900000416
Reverse weighting quality
Figure BDA00033163582900000417
Wherein,
Figure BDA00033163582900000418
for the co-directional component influence coefficient,
Figure BDA00033163582900000419
is an inverse component influence coefficient;
according to the couple balance mode, if the couple at the weighting surfaces a and b and the drop-off position m is 0, the couple is equal to
Figure BDA00033163582900000420
Solving the equation to obtain
Figure BDA0003316358290000051
Step 4, if alpha-beta is approximately equal to 90 degrees, the vibration fault point is close to the side A, and the corresponding fault position is
Figure BDA0003316358290000052
If alpha-beta is approximately equal to-90 degrees, the vibration fault point is close to the side A, and the corresponding fault position is
Figure BDA0003316358290000053
If it is
Figure BDA0003316358290000054
If the value is far greater than 1, the vibration variable is mainly the same direction component, and the corresponding fault point is located in the middle of the rotor.
And calculating and judging the vibration in the other direction on the same bearing according to the steps 1 to 4.
Corresponding to the method, the embodiment also provides a rotor sudden-change vibration fault positioning system, which comprises
The rotor sudden change front and back vibration vector recording module is used for recording the vibration vectors of the two ends of the rotor before sudden change in the same direction
Figure BDA0003316358290000055
And
Figure BDA0003316358290000056
abrupt change of vibration vector
Figure BDA0003316358290000057
And
Figure BDA0003316358290000058
a vibration variation calculating module for calculating vibration variation
Figure BDA0003316358290000059
Harmonic component decomposition module for the vibration variation
Figure BDA00033163582900000510
And
Figure BDA00033163582900000511
harmonic component decomposition
Figure BDA00033163582900000512
Figure BDA00033163582900000513
Wherein
Figure BDA00033163582900000514
The phase angle of (a) is alpha,
Figure BDA00033163582900000515
has a phase angle of beta;
wherein
Figure BDA00033163582900000516
The phase angle of (a) is alpha,
Figure BDA00033163582900000517
has a phase angle of beta;
as shown in FIG. 1, the mass m causes an additional centrifugal force F in the direction opposite to the drop-off position, which force F is equivalent to that at the weight plane a according to the force translation principle
Figure BDA00033163582900000518
And couple FLaIt can be considered that there are forces in the same magnitude and opposite directions in the plane b
Figure BDA00033163582900000519
Thus, in-phase component force is formed in the planes a and b
Figure BDA00033163582900000520
And couple of opposite phase components
Figure BDA00033163582900000521
(couple FLa with
Figure BDA00033163582900000522
In the opposite direction).
According to the harmonic component method, the rotor vibration at the working rotation speed is decomposed into in-phase (symmetrical) component vibration and anti-phase (anti-symmetrical) component vibration, the in-phase component is caused by first-order unbalance of the rotor, the anti-phase component vibration is caused by second-order unbalance (couple unbalance) of the rotor and accords with the orthogonal relation, and therefore in-phase weighting mass and anti-phase weighting mass are obtained.
Equidirectionally weighted mass
Figure BDA0003316358290000061
Reverse weighting quality
Figure BDA0003316358290000062
Wherein,
Figure BDA0003316358290000063
for the co-directional component influence coefficient,
Figure BDA0003316358290000064
is an inverse component influence coefficient;
according to the couple balance mode, if the couple at the weighting surfaces a and b and the drop-off position m is 0, the couple is equal to
Figure BDA0003316358290000065
Solving the equation to obtain
Figure BDA0003316358290000066
If alpha-beta is approximately equal to 90 degrees or alpha-beta is approximately equal to-90 degrees, the fault point judgment module indicates that the vibration fault point is close to the side A; if it is
Figure BDA0003316358290000067
If the value is far greater than 1, the vibration variable is mainly the same direction component, and the corresponding fault point is located in the middle of the rotor.
The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims (8)

1. The method for positioning the sudden change vibration fault of the rotor is characterized in that the symmetrical rotor comprises the rotor, a plurality of grade blades symmetrically fixed on the rotor and supporting points A, B; the support points A, B respectively provide support for two ends of the rotor; assuming that a certain level of blade falls off, the method for judging the position of the fault point comprises the following steps:
step 1, recording vibration vectors before sudden change of vibration at two ends of a rotor in the same direction
Figure FDA0003316358280000011
And
Figure FDA0003316358280000012
abrupt change of vibration vector
Figure FDA0003316358280000013
And
Figure FDA0003316358280000014
step 2, calculating vibration variation
Figure FDA0003316358280000015
Step 3, the vibration variation quantity is adjusted
Figure FDA0003316358280000016
And
Figure FDA0003316358280000017
harmonic component decomposition
Figure FDA0003316358280000018
Wherein
Figure FDA0003316358280000019
The phase angle of (a) is alpha,
Figure FDA00033163582800000110
has a phase angle of beta;
step 4, if alpha-beta is approximately equal to 90 degrees or alpha-beta is approximately equal to-90 degrees, the vibration fault point is close to the side A; if it is
Figure FDA00033163582800000111
If the value is far greater than 1, the vibration variable is mainly the same direction component, and the corresponding fault point is located in the middle of the rotor.
2. The method for locating the sudden rotor vibration fault according to claim 1, wherein the vibration in the other direction on the same rotor is calculated and judged according to steps 1 to 4.
3. The method for locating the sudden rotor vibration fault according to claim 1 or 2, wherein in the step 4, when the angle α - β ≈ 90 °, the fault position is
Figure FDA00033163582800000112
Wherein the distance between the falling point and the A side weighted plane is LaThe axial distance of the weighted planes on both sides of the supporting point A, B is L,
Figure FDA00033163582800000113
for the co-directional component influence coefficient,
Figure FDA00033163582800000114
is an inverse component influence coefficient.
4. The method for locating the sudden rotor vibration fault according to claim 3, wherein in the step 4, when the angle α - β ≈ -90 °, the fault position is
Figure FDA00033163582800000115
5. The rotor sudden change vibration fault location system of claim 1, wherein a symmetrical rotor comprises a rotor, a plurality of stage blades symmetrically fixed on the rotor, a support point A, B; the support points A, B respectively provide support for two ends of the rotor; assuming that a blade of a certain level is detached, the system for determining the position of the fault point includes:
the rotor sudden change front and back vibration vector recording module is used for recording the vibration vectors of the two ends of the rotor before sudden change in the same direction
Figure FDA0003316358280000021
And
Figure FDA0003316358280000022
abrupt change of vibration vector
Figure FDA0003316358280000023
And
Figure FDA0003316358280000024
a vibration variation calculating module for calculating vibration variation
Figure FDA0003316358280000025
Harmonic component decomposition module for the vibration variation
Figure FDA0003316358280000026
And
Figure FDA0003316358280000027
harmonic component decomposition
Figure FDA0003316358280000028
Figure FDA0003316358280000029
Wherein
Figure FDA00033163582800000210
The phase angle of (a) is alpha,
Figure FDA00033163582800000211
has a phase angle of beta;
if alpha-beta is approximately equal to 90 degrees or alpha-beta is approximately equal to-90 degrees, the fault point judgment module indicates that the vibration fault point is close to the side A; if it is
Figure FDA00033163582800000212
If the value is far greater than 1, the vibration variable is mainly the same direction component, and the corresponding fault point is located in the middle of the rotor.
6. The system for locating sudden rotor vibration fault according to claim 5, wherein vibration in another direction on the same rotor is calculated and judged according to steps 1-4.
7. The rotor sudden-change vibration fault location system according to claim 5 or 6, wherein in the fault point judgment module, when α - β ≈ 90 °, the fault position is
Figure FDA00033163582800000213
Wherein the distance between the falling point and the A side weighted plane is LaThe axial distance of the weighted planes on both sides of the supporting point A, B is L,
Figure FDA00033163582800000214
for the co-directional component influence coefficient,
Figure FDA00033163582800000215
is an inverse component influence coefficient.
8. The method for locating the sudden rotor vibration fault according to claim 7, wherein in the fault point judgment module, when the angle α - β ≈ -90 °, the fault position is
Figure FDA00033163582800000216
CN202111232415.8A 2021-10-22 2021-10-22 Rotor sudden-change vibration fault positioning method and system Withdrawn CN114061729A (en)

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102095561A (en) * 2010-12-01 2011-06-15 浙江省电力试验研究院 Falling fault positioning method for rotating part of large-size steam turbine
US20140230555A1 (en) * 2012-12-20 2014-08-21 Zapadoceska Univerzita V Plzni Method of detecting and localizing partial rotor-stator rubbing during the operation of a turbine
CN110231161A (en) * 2019-07-12 2019-09-13 中国大唐集团科学技术研究院有限公司华东电力试验研究院 Single-span rotor fault position diagnostic method and system based on three-dimensional system of coordinate

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102095561A (en) * 2010-12-01 2011-06-15 浙江省电力试验研究院 Falling fault positioning method for rotating part of large-size steam turbine
US20140230555A1 (en) * 2012-12-20 2014-08-21 Zapadoceska Univerzita V Plzni Method of detecting and localizing partial rotor-stator rubbing during the operation of a turbine
CN110231161A (en) * 2019-07-12 2019-09-13 中国大唐集团科学技术研究院有限公司华东电力试验研究院 Single-span rotor fault position diagnostic method and system based on three-dimensional system of coordinate

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* Cited by examiner, † Cited by third party
Title
刘宝富 等: "基于TDM的汽轮发电机组轴承振动异常分析", 《沈阳工程学院学报(自然科学版)》 *
应光耀 等: "基于谐分量法的汽轮机叶片飞脱故障定位方法研究及应用", 《动力工程学报》 *

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Application publication date: 20220218