CN103712746A - Method for solving mechanical lag angle in rotor dynamic balance test - Google Patents
Method for solving mechanical lag angle in rotor dynamic balance test Download PDFInfo
- Publication number
- CN103712746A CN103712746A CN201410008820.5A CN201410008820A CN103712746A CN 103712746 A CN103712746 A CN 103712746A CN 201410008820 A CN201410008820 A CN 201410008820A CN 103712746 A CN103712746 A CN 103712746A
- Authority
- CN
- China
- Prior art keywords
- vibration
- phase
- rotor
- high point
- signal
- 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
Landscapes
- Testing Of Balance (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to a method for solving a mechanical lag angle in a rotor dynamic balance test. An electrical vortex sensor, a phase demodulation sensor and a vibrating sensor are arranged on a rotor system, the vibration amplitude and the phase of a rotor during rotation are measured by a dynamic signal analysis meter system, and the mechanical lag angle and an overweight phase angle of the rotor are calculated according to the test result. The method for solving the mechanical lag angle in the rotor dynamic balance test is characterized in that the rotor can operate forwardly and reversely once respectively at the same rotating speed without adding test mass and lower than a critical rotation speed, and the measured vibration value and the phase value are used for calculating the mechanical lag angle and the overweight phase angle.
Description
Technical field:
The present invention relates to the acquiring method of relevant Hysteresis phase lag in a kind of dynamic balance test of rotor.
Background technology:
In dynamic balance test of rotor, all need to test out the Hysteresis phase lag of rotor, by Hysteresis phase lag, determined the phasing degree that adds counterweight, whether Hysteresis phase lag test accurately directly affects precision and the success or failure of dynamic balance running.
Generally working speed lower than the rotor of critical rotary speed rigid rotator, working speed is higher than the flex rotor that cries of critical rotary speed.Rigid rotator need to be determined Hysteresis phase lag by adding test mass, adds each operation of rotor of test mass front and back once, then calculating machine drag angle.Flex rotor can not add test mass just can determine Hysteresis phase lag and overweight angle, but will in critical rotary speed, move and could determine, because at this moment Hysteresis phase lag equals 90 degree, can determine the phasing degree that adds counterweight thus.But rotor vibrates when the critical rotary speed excessively sometimes, can not record phasing degree accurately.Therefore how on the rotating speed lower than critical rotary speed, and need not add the phase place that test mass just can accurately determine Hysteresis phase lag and add counterweight and just become extremely important.
Summary of the invention:
The object of this invention is to provide a kind of good reliability, measuring accuracy high, can realize on the rotating speed lower than critical rotary speed, and need not add the method that test mass just can accurately be determined Hysteresis phase lag and add the phase place of counterweight.The subject matter that the present invention will solve is the transient equilibrium of generator amature.The object of the invention is to be achieved through the following technical solutions: the present invention is the acquiring method of relevant Hysteresis phase lag in a kind of dynamic balance test of rotor, and concrete steps are:
1) in armature spindle bearing, arrange low-frequency shock transducer and current vortex sensor, and make them
In alignment vertically, in rotating shaft, arrange phase demodulation sheet, phase demodulation sheet will with phase demodulation sensor in the same horizontal line, the vibration signal of low-frequency shock transducer picker shaft bearing, current vortex sensor picks up throw signal and the phase signal of rotating shaft;
2) connect measuring system, vibration, throw and phase signal are connected to data acquisition system (DAS), data acquisition system (DAS) is connected to computing machine;
3) start computing machine, operation state signal analysis software;
4) rotor is rotated, in the situation that vibrating and throw does not exceed standard, the rotor for working speed lower than critical rotary speed, rotating speed should approach working speed as much as possible, the rotor for working speed higher than critical rotary speed, rotating speed should approach critical rotary speed as much as possible;
5) data acquisition system (DAS) gathers signal, and computing machine compares analysis to time domain waveform and the frequency domain figure of the vibration, throw and the phase signal that gather, obtains amplitude and the phase place frequently of turning of each measuring point vibration and throw signal;
6) rotor is rotated, with step 4) the identical switched in opposite of rotating speed, repeat 4) to 5) step;
7) through above-mentioned test, obtain vibration and throw signal, vibration signal and throw signal are used for calculating machine drag angle (4), supposes from phase demodulation sheet (5) position, and phasing degree, for just, is to bear clockwise counterclockwise, and phasing degree, phase demodulation sheet position is zero,
8) twice operation due to rotor is along different directions, by counterclockwise operation, records the first high point of vibration (2), by clockwise operation, records the second high point of vibration (3), the phase place of the first high point of vibration (2)
the phasing degree between the first high point of vibration (2) and phase demodulation sheet (5), the phase place of the second high point of vibration (3)
the phasing degree between the second high point of vibration (3) and phase demodulation sheet (5),
9) relative position of the first high point of vibration (2), the second vibration high point (3) and phase demodulation sheet (5) is drawn on rotor sectional view, position, middle at the first high point of vibration (2) and the second high point of vibration (3) is exactly overweight angle (1), overweight angle (1) is exactly Hysteresis phase lag (4) to the phasing degree of arbitrary high point, is formulated as:
Hysteresis phase lag (4):
Overweight angle (1) equals:
Wherein: θ is Hysteresis phase lag, unit: degree,
10) by test result calculations, gone out Hysteresis phase lag and the overweight angle of rotor, thereby determine the direction that adds counterweight, complete dynamic balance running.
Technique effect: use the present invention not adding test mass and obtain the Hysteresis phase lag of rotor under the rotating speed lower than critical rotary speed, thereby determine the phase place that should add counterweight, complete dynamic balance running.Rotor is when operation, due to the existence of damping, it vibrates peaked point (being called high point) is not same point with the overweight point of rotor, when rotating speed is lower, the two is more approaching, when rotating speed equals critical rotary speed, both differ 90 degree, when rotating speed surpasses and during away from critical rotary speed, both differ and approach 180 degree, rotor dynamic balancing system is after installation, and its Hysteresis phase lag is only relevant with rotating speed, when the rotation of rotor clockwise direction is rotated with counter clockwise direction.Because other conditions of unit do not change, just sense of rotation has changed, so its Hysteresis phase lag is identical under these two kinds of operating modes.In Fig. 1, suppose that (5) are for phase demodulation sheet position (phase place be zero), (1) point is the overweight point of rotor, phase place is counterclockwise for just.When unit counterclockwise rotates, record vibration high point (2) phase place and be
when unit clockwise direction is rotated, record vibration high point (3) phase place and be
Hysteresis phase lag:
Overweight angle:
Rigid rotator need to be determined Hysteresis phase lag by adding test mass, adds each operation of rotor of test mass front and back once, then calculating machine drag angle, great little test result is had a significant impact of adding an examination of, test mass adds little, and test result is inaccurate, strengthened, can make rotor-support-foundation system produce very large vibration.Flex rotor can not add test mass just can determine Hysteresis phase lag and overweight angle, but will in critical rotary speed, move and could determine, because at this moment Hysteresis phase lag equals 90 degree, can determine the phasing degree that adds counterweight thus.But rotor vibrates when the critical rotary speed excessively sometimes, can not record phasing degree accurately.Therefore how on the rotating speed lower than critical rotary speed, and need not add the phase place that test mass just can accurately determine Hysteresis phase lag and add counterweight and just become extremely important.Method of the present invention can be avoided the generation of the problems referred to above, and method is easy, and easily, result is accurate in test.
Accompanying drawing explanation:
Fig. 1 phase relation key diagram
Fig. 2 test macro connection layout
Embodiment:
As shown in Figure 2, the acquiring method of relevant Hysteresis phase lag in a kind of dynamic balance test of rotor, method comprises the steps:
1) in armature spindle bearing, arrange low-frequency shock transducer and current vortex sensor, and make them in alignment vertically, in rotating shaft, arrange phase demodulation sheet, phase demodulation sheet will with phase demodulation sensor in the same horizontal line, the vibration signal of low-frequency shock transducer picker shaft bearing, current vortex sensor picks up throw signal and the phase signal of rotating shaft;
2) connect measuring system, vibration, throw and phase signal are connected to data acquisition system (DAS), data acquisition system (DAS) is connected to computing machine;
3) start computing machine, operation state signal analysis software;
4) rotor is rotated, in the situation that vibrating and throw does not exceed standard, the rotor for working speed lower than critical rotary speed, rotating speed should approach working speed as much as possible, the rotor for working speed higher than critical rotary speed, rotating speed should approach critical rotary speed as much as possible;
5) data acquisition system (DAS) gathers signal, and computing machine compares analysis to time domain waveform and the frequency domain figure of the vibration, throw and the phase signal that gather, obtains amplitude and the phase place frequently of turning of each measuring point vibration and throw signal;
6) rotor is rotated, with step 4) the identical switched in opposite of rotating speed, repeat 4) to 5) step;
7) through above-mentioned test, obtain vibration and throw signal, vibration signal and throw signal are used for calculating machine drag angle, supposes from phase demodulation sheet 5 positions, and phasing degree, for just, is to bear clockwise counterclockwise, and phasing degree, phase demodulation sheet position is zero,
8) twice operation due to rotor is along different directions, by counterclockwise operation, records the high point 2 of the first vibration, recorded the phase place of the high point 2 of high point 3, the first vibration of the second vibration by clockwise operation
the phasing degree between the high point 2 of the first vibration and phase demodulation sheet 5, the phase place of the high point 3 of the second vibration
the phasing degree between the high point 3 of the second vibration and phase demodulation sheet 5,
9) relative position of the high point high point 3 of the 2, second vibration of the first vibration and phase demodulation sheet 5 is drawn on rotor sectional view, position, middle at the high point 3 of high point the 2 and second vibration of the first vibration is exactly overweight angle 1, overweight angle 1 is exactly Hysteresis phase lag 4 to the phasing degree of arbitrary high point, is formulated as:
Hysteresis phase lag:
Overweight angle 1 equals:
Wherein: θ is Hysteresis phase lag 4, unit: degree,
be the phase place of the high point 2 of the first vibration, unit: degree,
10) by test result calculations, gone out Hysteresis phase lag and the overweight angle of rotor, thereby determine the direction that adds counterweight, complete dynamic balance running.
General rotor is all unbalanced, and when rotor operation, we can measure amplitude and the phase place of its vibration and throw, phase place with respect to phase demodulation sheet that, the phase place of phase demodulation sheet position is zero, from phase demodulation sheet, counterclockwise angle is for just, and clockwise angle is for bearing.It vibrates peaked point and is called high point, with the overweight point of rotor be not same point, during actual test, we can only directly measure the phase place of the high point of vibration, Hysteresis phase lag and overweight phasing degree can only be obtained by calculating.
As shown in Figure 1, on rotor sectional view, phase place with respect to phase demodulation sheet 4 that, the phase place of phase demodulation sheet position is zero, counterclockwise phase place is for just, and phase place, for bearing, is rotated counterclockwise rotor clockwise, record the high point 2 of the first vibration, then turn clockwise, record the high point 3 of the second vibration, because rotating speed is constant, be opposite direction, so Hysteresis phase lag is identical:
Hysteresis phase lag:
Overweight angle:
By test result calculations, gone out Hysteresis phase lag and the overweight angle of rotor, thereby determine the direction that adds counterweight, complete dynamic balance running.
Test run result of the present invention proves:
By this measurement mechanism and method, can not add test mass, and at the Hysteresis phase lag lower than accurate acquisition rotor under critical rotary speed, thereby determine the phase place that adds counterweight, complete rotor dynamic balancing work.
Claims (1)
1. an acquiring method for Hysteresis phase lag in dynamic balance test of rotor, is characterized in that: method comprises the steps:
1) in armature spindle bearing, arrange low-frequency shock transducer and current vortex sensor, and make them in alignment vertically, in rotating shaft, arrange phase demodulation sheet, phase demodulation sheet will with phase demodulation sensor in the same horizontal line, the vibration signal of low-frequency shock transducer picker shaft bearing, current vortex sensor picks up throw signal and the phase signal of rotating shaft;
2) connect measuring system, vibration, throw and phase signal are connected to data acquisition system (DAS), data acquisition system (DAS) is connected to computing machine;
3) start computing machine, operation state signal analysis software;
4) rotor is rotated, in the situation that vibrating and throw does not exceed standard, the rotor for working speed lower than critical rotary speed, rotating speed should approach working speed as much as possible, the rotor for working speed higher than critical rotary speed, rotating speed should approach critical rotary speed as much as possible;
5) data acquisition system (DAS) gathers signal, and computing machine compares analysis to time domain waveform and the frequency domain figure of the vibration, throw and the phase signal that gather, obtains amplitude and the phase place frequently of turning of each measuring point vibration and throw signal;
6) rotor is rotated, with step 4) the identical switched in opposite of rotating speed, repeat 4) to 5) step;
7) through above-mentioned test, obtain vibration and throw signal, vibration signal and throw signal are used for calculating machine drag angle (4), supposes from phase demodulation sheet (5) position, and phasing degree, for just, is to bear clockwise counterclockwise, and phasing degree, phase demodulation sheet position is zero,
8) twice operation due to rotor is along different directions, by counterclockwise operation, records the first high point of vibration (2), by clockwise operation, records the second high point of vibration (3), the phase place of the first high point of vibration (2)
the phasing degree between the first high point of vibration (2) and phase demodulation sheet (5), the phase place of the second high point of vibration (3)
the phasing degree between the second high point of vibration (3) and phase demodulation sheet (5),
9) relative position of the first high point of vibration (2), the second vibration high point (3) and phase demodulation sheet (5) is drawn on rotor sectional view, position, middle at the first high point of vibration (2) and the second high point of vibration (3) is exactly overweight angle (1), overweight angle (1) is exactly Hysteresis phase lag (4) to the phasing degree of arbitrary high point, is formulated as:
Hysteresis phase lag (4):
Overweight angle (1) equals:
Wherein: θ is Hysteresis phase lag, unit: degree,
10) by test result calculations, gone out Hysteresis phase lag and the overweight angle of rotor, thereby determine the direction that adds counterweight, complete dynamic balance running.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410008820.5A CN103712746B (en) | 2014-01-09 | 2014-01-09 | The acquiring method of Hysteresis phase lag in a kind of dynamic balance test of rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410008820.5A CN103712746B (en) | 2014-01-09 | 2014-01-09 | The acquiring method of Hysteresis phase lag in a kind of dynamic balance test of rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103712746A true CN103712746A (en) | 2014-04-09 |
| CN103712746B CN103712746B (en) | 2016-03-16 |
Family
ID=50405900
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410008820.5A Expired - Fee Related CN103712746B (en) | 2014-01-09 | 2014-01-09 | The acquiring method of Hysteresis phase lag in a kind of dynamic balance test of rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103712746B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104977124A (en) * | 2015-07-06 | 2015-10-14 | 沈阳申克动力机械有限公司 | Complete dynamic balance type coupling |
| CN106092445A (en) * | 2016-08-11 | 2016-11-09 | 大唐长春第二热电有限责任公司 | Vector triangle calculates the method that method looks for rotor dynamic balancing |
| CN107063571A (en) * | 2017-06-09 | 2017-08-18 | 山东钢铁股份有限公司 | The balancing weight installation site measurement apparatus of dynamic balance running |
| CN106100248B (en) * | 2016-08-23 | 2018-06-01 | 中国大唐集团科学技术研究院有限公司华东分公司 | A kind of method whether inspection electric machine stand firmly installs |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5431049A (en) * | 1994-06-27 | 1995-07-11 | Ford Motor Company | Vehicle driveline balancing |
| WO2005042959A2 (en) * | 2003-09-19 | 2005-05-12 | The Boeing Company | Engine balancing system and method |
| CN101929908A (en) * | 2008-12-08 | 2010-12-29 | 广东省电力工业局试验研究所 | Unbalanced azimuth estimation method based on holo-spectrum technology |
| CN102564698A (en) * | 2011-12-21 | 2012-07-11 | 浙江省电力试验研究院 | Multi-rotor joint vibration mode balancing method for single support shafting steam turbine generator unit |
-
2014
- 2014-01-09 CN CN201410008820.5A patent/CN103712746B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5431049A (en) * | 1994-06-27 | 1995-07-11 | Ford Motor Company | Vehicle driveline balancing |
| WO2005042959A2 (en) * | 2003-09-19 | 2005-05-12 | The Boeing Company | Engine balancing system and method |
| CN101929908A (en) * | 2008-12-08 | 2010-12-29 | 广东省电力工业局试验研究所 | Unbalanced azimuth estimation method based on holo-spectrum technology |
| CN102564698A (en) * | 2011-12-21 | 2012-07-11 | 浙江省电力试验研究院 | Multi-rotor joint vibration mode balancing method for single support shafting steam turbine generator unit |
Non-Patent Citations (3)
| Title |
|---|
| 王维民等: "旋转机械无试重现场动平衡原理与应用", 《振动与冲击》 * |
| 钱广华: "《石油和化工设备技术和管理论文集》", 29 February 2012, 中国石化出版社 * |
| 阙广庆: "一种高转速水轮发电机转子动平衡的试验方法", 《大电机技术》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104977124A (en) * | 2015-07-06 | 2015-10-14 | 沈阳申克动力机械有限公司 | Complete dynamic balance type coupling |
| CN104977124B (en) * | 2015-07-06 | 2017-12-12 | 沈阳申克动力机械有限公司 | Complete dynamic balancing shaft coupling |
| CN106092445A (en) * | 2016-08-11 | 2016-11-09 | 大唐长春第二热电有限责任公司 | Vector triangle calculates the method that method looks for rotor dynamic balancing |
| CN106100248B (en) * | 2016-08-23 | 2018-06-01 | 中国大唐集团科学技术研究院有限公司华东分公司 | A kind of method whether inspection electric machine stand firmly installs |
| CN107063571A (en) * | 2017-06-09 | 2017-08-18 | 山东钢铁股份有限公司 | The balancing weight installation site measurement apparatus of dynamic balance running |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103712746B (en) | 2016-03-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Yamamoto et al. | A smart experimental setup for vibration measurement and imbalance fault detection in rotating machinery | |
| CN102155984B (en) | General vibration signal measuring system of fan | |
| CN102564698B (en) | Multi-rotor joint vibration mode balancing method for single support shafting steam turbine generator unit | |
| CN103115726B (en) | Rotating parts and components dynamic balance method based on strain | |
| JPH0141804B2 (en) | ||
| CN103712746B (en) | The acquiring method of Hysteresis phase lag in a kind of dynamic balance test of rotor | |
| CN105067106B (en) | A kind of intershaft bearing vibration signals collecting method | |
| CN103542967A (en) | Positioning torque measurement device | |
| CN106655959A (en) | Method for measuring rotation speed of brushless direct-current motor | |
| CN104101464B (en) | Multi-wheel-disc rotor dynamic balancing test method based on rotating coordinate system | |
| CN108348930A (en) | Centrifugal separator | |
| CN103105266A (en) | Dynamic balance method of bending moment of rotating mechanical rotor biplane | |
| JP2013213817A (en) | Systems and methods of identifying types of faults | |
| CN102778335A (en) | Anisotropic rotor holographic dynamic balancing method based on equivalent initial phase vector | |
| CN104330214B (en) | Simple field dynamic balancing method | |
| CN103698088A (en) | Testing method for asymmetric rigidity of turbonator rotating shaft | |
| CZ2011588A3 (en) | Method of determining actual eccentricity of a rotating rotor and rotating rotor eccentricity diagnostics | |
| KR100941467B1 (en) | Dynamic Balancing Apparatus and Methods using a Linear Time-varying Angular Velocity Model | |
| CN104977126A (en) | Method and system for detecting and calculating dynamic unbalance of main shaft | |
| CN103674430A (en) | Dynamic balancing tool holder and dynamic balancing control system of processor | |
| CN203785840U (en) | Rotor balance experiment table | |
| CN102928611A (en) | Second harmonic generation-based method for obtaining critical rotation speed of steam turbine rotor | |
| CN105547591A (en) | Asymmetric rotor balancing method without phase position | |
| CN109847952B (en) | Dynamic balance method of double-shaft precision centrifuge turntable based on driving current | |
| CN204575249U (en) | A kind of fast adjuster of enclosure space internal rotor amount of unbalance |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160316 Termination date: 20180109 |