CN109974849A - Without under reference signal based on the blade vibration on-line monitoring method of Tip-Timing technology - Google Patents
Without under reference signal based on the blade vibration on-line monitoring method of Tip-Timing technology Download PDFInfo
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- CN109974849A CN109974849A CN201910263644.2A CN201910263644A CN109974849A CN 109974849 A CN109974849 A CN 109974849A CN 201910263644 A CN201910263644 A CN 201910263644A CN 109974849 A CN109974849 A CN 109974849A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
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Abstract
Blade vibration on-line monitoring method based on Tip-Timing technology under a kind of no reference signal, blade angle when reaching time and the arrival for the sensor that each is arranged radially according to the blade of actual measurement, approximation obtains the theoretical time that blade reaches sensor by way of fitting of a polynomial, the revolving speed and sensor angles of equal value of rotor are obtained further according to the highest order of fitting, and the vibration offset of blade tip is calculated by the measured time that blade reaches sensor, blade vibration parameter identification is finally carried out in the way of Sine-Fitting, realizes on-line monitoring.The present invention can guarantee without reference to signal, still be able to be monitored the vibration of blade, reduce the cost of blade vibration on-line monitoring, improve the reliability of Tip-Timing technology on-line monitoring.
Description
Technical field
The present invention relates to a kind of technology of aero-engine manufacturing field, specifically a kind of nothing for turbomachine
Based on the blade vibration on-line monitoring method of Tip-Timing technology under reference signal.
Background technique
Acting component of the blade as turbomachine is motivated in operation by various load so as to cause blade vibration.
Blade vibration is a problem very serious in turbomachine, because vibration is excessive to likely result in blade fatigue failure.Cause
This, blade vibration on-line monitoring is essential.The form of blade vibration can be divided into two according to frequency and the relationship of revolving speed
Major class: synchronous vibration and asynchronous vibration.Synchronous vibration refer to vibration frequency of blade and rotor speed at integral multiple relation, usually
As caused by the wake flow excitation of the guide vane or stator blade of blade upstream.Asynchronous vibration refers to vibration frequency of blade and rotor speed
At non-integral multiple relationship, usually occur in rotating stall, the special operation conditions such as surge or flutter.
Common blade vibration parameter identification method includes single parameter method, two parameter method, autoregression method, Sine-Fitting etc.
Deng.But these methods the case where being all based on reference signal, i.e. revolving speed speed during rotor turns around does not occur
Variation.If cannot identify blade vibration parameter in the case where failing without reference to signal or reference signal.In addition,
If rotation speed change is too fast, above-mentioned traditional Tip-Timing method can also fail.Therefore, development is without reference to blade under signal
Vibration online monitoring is of great significance.
Summary of the invention
The present invention In view of the above shortcomings of the prior art, proposes under a kind of no reference signal based on Tip-Timing technology
Blade vibration on-line monitoring method, can guarantee without reference to signal, still be able to vibration to blade into
Row monitoring, reduces the cost of blade vibration on-line monitoring, improves the reliability of Tip-Timing technology on-line monitoring.
The present invention is achieved by the following technical solutions:
The blade angle when present invention reaches time and the arrival for the sensor that each is arranged radially according to the blade of actual measurement,
Approximation obtains the theoretical time that blade reaches sensor by way of fitting of a polynomial, obtains further according to the highest order of fitting
The revolving speed of rotor and sensor angles of equal value, and calculate by the measured time of blade arrival sensor the vibration of blade tip
Dynamic offset, finally carries out blade vibration parameter identification in the way of Sine-Fitting, realizes on-line monitoring.
The mode of the fitting of a polynomial refers to: the measured time that each blade in each circle reaches sensor is measured,
Time and the blade angle progress fitting of a polynomial f=a0+a1x+a2 that blade reaches sensor are obtained to actual measurement
x2+a3·x3+ ..., suitable fitting order is selected according to polynomial coefficient (a0, a1, a2 ...), so that approximation obtains blade reason
By the functional relation reached between sensor time and angle.
The revolving speed of the rotor and sensor angles of equal value, are judged by the highest order m of fitting of a polynomial:
As m=1, there is no variation, as constant in this circle, sensor setting angle of equal value is equal to original rotor speed
Sensor setting angle；As m > 1, rotor speed is variable in this circle, by calculating the transient speed of each angle and right
The sensor angles of equal value answered obtain.
Technical effect
Compared with prior art, the present invention can guarantee without reference to signal, still be able to blade
Vibration is monitored, and reduces the cost of blade vibration on-line monitoring, improves the reliability of Tip-Timing technology on-line monitoring.
Detailed description of the invention
Fig. 1 is Tip-Timing technical schematic diagram；
Fig. 2 is the blade vibration on-line monitoring method flow chart under no reference signal based on Tip-Timing technology；
Fig. 3 is embodiment schematic diagram；
Fig. 4 is the revolving speed obtained under reference signal and the speed diagram obtained under no reference signal；
Fig. 5 is the relative error figure for the revolving speed that the revolving speed obtained under reference signal is obtained with no reference signal；
Fig. 6 is No. 1 blade amplitude image obtained under the obtained No. 1 blade amplitude of reference signal and no reference signal；
Fig. 7 is that No. 1 blade amplitude that reference signal obtains and the opposite of No. 1 blade amplitude obtained under no reference signal are missed
Difference figure；
In figure: the input of 1 reference signal, 2 Tip timing sensors, 3 casings, 4 blades, 5 Laser emission receivers, 6 timing
Device, 7 monitoring modulars, a blade deviation post, b blade balance position, r impeller radius.
Specific embodiment
As shown in Fig. 2, to be related to the blade vibration based on Tip-Timing technology under a kind of no reference signal online for the present embodiment
Monitoring method, comprising the following steps:
1. blade is actually reached each time for being arranged radially sensor (preferably in insertion casing)Blade and sensor are numbered in the present embodiment: blade is from 1 to N, sensor
From 1 to j, that is, indicate that i-th blade is actually reached the time of j-th of sensor, x indicates first that the 2nd sensor is recorded
A blade arrival time is blade x, and first blade arrival time that y indicates that j-th of sensor is recorded is blade y.
Each blade reaches the point of theory of each the sensor
Wherein: ψjIndicate the quantity of blade between sensing j and sensor 1,θjIndicate the installation of j-th of sensor
Angle, θ ojIndicate sensor j and the blade the distance between nearest apart from it:
2. blade actual time of arrival and blade angle carry out fitting of a polynomial, highest fitting is determined according to fitting coefficient
Order, and acquire functional relation:Wherein:Indicate that blade theory reaches the time of sensor.
1) it is equal to 1 when highest is fitted order, that is, shows that blade actual time of arrival and blade angle are linear at this time,
It can thus be understood that rotor speed is constant in this circle, i.e.,
2) it is greater than 1 when highest is fitted order, that is, shows that blade actual time of arrival and blade angle at non-linear relation, turn
Rotor speed is variation in this circle, then accordingly solves inverse function relationship: β=f-1(t), remember f-1For G, it may be assumed that β=G (t) leads to
Cross and ask G that can obtain the single order inverse of t: v=G ' (t), then the sensor setting angle of corresponding equivalence is equal to:Its
In: veConstant rotational speed value required for sensor j is reached in indicating rotor at the same time.
3. solving blade tip according to the revolving speed of calculating and time difference vibrates offset, specifically: fitting highest order etc.
In 1:And fitting highest order is greater than
Steady-state vibration d=Asin (ω t+ φ of the blade under single driving source0), in which: A is amplitude, and ω indicates vibration
Dynamic frequency, φ0Indicate initial phase, when introducing dimensionless group EO (vibration frequency multiplication), then steady-state vibration is rewritten into: Wherein: θ indicates that the setting angle of sensor, v indicate rotary speed of rotator, veIndicate etc.
The rotary speed of rotator of valence, i.e., in the same time, blade, which reaches, senses required constant rotational speed value.
4. blade vibration parameter is calculated by the way of Sine-Fitting, specifically: the θ when being fitted highest order and being equal to 1ej=θj, because
This Sine-Fitting based on least square method can with unified representation at:
In the present embodiment the quantity of sensor be 3 or more, when number of sensors be equal to 3, then motivated in advance by Campbell chart
Order EO, accordingly obtain the amplitude that blade vibration parameter includes: blade iBlade i equilbrium position ci=
ai0；The vibration initial phase of blade i
As shown in figure 3, the present embodiment is verified by following environment: experimental subjects is the aerofoil fan of five blades,
By three laser sensors 2 on the casing 3 and sensor arrangement angle is respectively 20 °, 60 °, 100 °, and sent out respectively with laser
It penetrates receiver 5 to be connected, the laser pick-off signal triggering timing device 6 of Laser emission receiver 5, the time that blade reaches sensor will
It is recorded and is transferred in monitoring modular 7 and analyzed.The experimental result of 1000 turns of front is taken to compare and analyze.
To in a certain circle blade arrival time and blade angle carry out fitting of a polynomial analysis, if table 1 is it can be found that two
Higher order term fitting coefficient more than rank is very small, and increases fitting order and do not have a significant effect to the goodness of fit.Therefore root
According to fitting coefficient, suitable highest fitting order can choose.
Table 1
According to the fitting result of each circle, corresponding revolving speed is calculated.It the revolving speed that is measured in Fig. 5 and is obtained by fitting result
Speed error is lower than 0.08%.Revolving speed relative error
As shown in fig. 6, the relative error for the amplitude that the calculating amplitude acquired by the revolving speed measured and the revolving speed of fitting acquireWhole relative error is lower than 6%.
Technology one of of the Tip-Timing technology as non-contacting blade oscillation measurement, is widely used in compressor, whirlpool
The turbomachines equipment such as wheel.It is supervised online to solve the blade vibration without reference to signal or reference signal failure
It surveys, the time can be actually reached by the blade to each circle and blade angle carries out fitting of a polynomial, approximation obtains blade
Theoretical arrival time.Then it according to the highest order of fitting, carries out corresponding revolving speed and calculates and sensor established angle of equal value
It calculates.Finally by the vibration amplitude that sensor angles and sensor of equal value measure, the sine based on least square method is utilized
Fitting solves and obtains the vibration information of blade.
Using five blade axial-flow fans, the rotor speed acquired using reference signal, leaf have been obtained by way of experiment
Piece amplitude；And without reference to signal, rotor speed, blade amplitude have been obtained using the present invention.According to opposite
Error analysis as a result, demonstrating feasibility and correctness of the invention.
Above-mentioned specific implementation can by those skilled in the art under the premise of without departing substantially from the principle of the invention and objective with difference
Mode carry out local directed complete set to it, protection scope of the present invention is subject to claims and not by above-mentioned specific implementation institute
Limit, each implementation within its scope is by the constraint of the present invention.
Claims (8)
1. based on the blade vibration on-line monitoring method of Tip-Timing technology under a kind of no reference signal, which is characterized in that according to
The blade angle when blade of actual measurement reaches time and the arrival for the sensor that each is arranged radially, passes through the side of fitting of a polynomial
Formula approximation obtains the theoretical time that blade reaches sensor, obtains the revolving speed and equivalence of rotor further according to the highest order of fitting
Sensor angles, and the vibration offset of blade tip is calculated by the measured time that blade reaches sensor, finally utilize
The mode of Sine-Fitting carries out blade vibration parameter identification, realizes on-line monitoring.
2. according to the method described in claim 1, it is characterized in that, the mode of the fitting of a polynomial refers to: measuring each circle
In each blade reach measured time of sensor, time and the blade angle that blade reaches sensor are obtained to actual measurement
Carry out fitting of a polynomial f=a0+a1x+a2x2+a3·x3+ ..., it selects to close according to polynomial coefficient (a0, a1, a2...)
Suitable fitting order, so that approximate obtain the functional relation between blade theory arrival sensor time and angle.
3. according to the method described in claim 1, it is characterized in that, the revolving speed of the rotor and sensor angle of equal value
Degree, is judged by the highest order m of fitting of a polynomial: as m=1, there is no variations in this circle for rotor speed, i.e.,
For constant, sensor setting angle of equal value is equal to original sensor setting angle；As m > 1, rotor speed is in this circle
For variable, obtained by the transient speed of each angle of calculating and the sensor angles of corresponding equivalence.
4. according to the method described in claim 1, it is characterized in that, described being arranged radially refer to insertion casing in.
5. according to the method described in claim 1, it is characterized in that, the blade is actually reached each and is arranged radially sensor
TimeBlade and sensor are numbered in the present embodiment: blade is passed from 1 to N
Sensor indicates that i-th blade is actually reached the time of j-th of sensor, x indicates what the 2nd sensor was recorded from 1 to j
First blade arrival time is blade x, and first blade arrival time that y indicates that j-th of sensor is recorded is blade y；
Each blade reaches the point of theory of each the sensor:
Wherein: ψjIndicate blade between sensing j and sensor 1
Quantity,θjIndicate the established angle of j-th of sensor, θojIndicate sensor j and the leaf nearest apart from it
The distance between piece:
6. according to the method described in claim 5, it is characterized in that, it is quasi- that blade actual time of arrival and blade angle carry out multinomial
It closes, highest fitting order is determined according to fitting coefficient, and acquire functional relation:Wherein:Indicate that blade theory arrives
Up to the time of sensor；
1) it is equal to 1 when highest is fitted order, that is, shows that blade actual time of arrival and blade angle are linear at this time, that is, turn
Rotor speed is constant in this circle, i.e.,
2) it is greater than 1 when highest is fitted order, that is, shows blade actual time of arrival and blade angle into non-linear relation, rotor turns
Speed is variation in this circle, then accordingly solves inverse function relationship: β=f-1(t), note f1 is G, it may be assumed that β=G (t), by seeking G
Can obtain to the single order inverse of t: v=G ' (t), then the sensor setting angle of corresponding equivalence is equal to:Wherein: ve
Constant rotational speed value required for sensor j is reached in indicating rotor at the same time.
7. according to the method described in claim 5, it is characterized in that, according to the method described in claim 5, it is characterized in that, according to meter
The revolving speed of calculation and time difference solve blade tip and vibrate offset, specifically: fitting highest order is equal to 1: And fitting highest order is greater than 1:
Steady-state vibration d=Asin (ω t+ φ of the blade under single driving source0), in which: A is amplitude, and ω indicates vibration frequency
Rate, φ0Indicate initial phase, when introducing dimensionless group EO, then steady-state vibration is rewritten into:
Wherein: θ indicates that the setting angle of sensor, v indicate rotary speed of rotator, veIndicate rotary speed of rotator of equal value, i.e., in phase
With in the time, blade reaches constant rotational speed value required for sensing.
8. according to the method described in claim 7, it is characterized in that, blade vibration parameter is calculated by the way of Sine-Fitting, have
Body are as follows: the θ when being fitted highest order and being equal to 1ej=θj, therefore the Sine-Fitting based on least square method can with unified representation at:When number of sensors be equal to 3, then pass through Campbell chart in advance
The order EO motivated accordingly obtains the amplitude that blade vibration parameter includes: blade iBlade i balance position
Set ci=ai0；The vibration initial phase of blade i
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110307894A (en) * | 2019-07-12 | 2019-10-08 | 天津大学 | Based on the shrouded blade vibration measuring method and calibration system for improving Tip-Timing principle |
| CN110851963A (en) * | 2019-10-25 | 2020-02-28 | 西安交通大学 | Casing circumferential arrangement method of blade end timing sensor |
| CN111323190A (en) * | 2020-04-13 | 2020-06-23 | 北京化工大学 | Measuring method and measuring device for five-dimensional vibration of rotating blade |
| CN111579060A (en) * | 2020-06-28 | 2020-08-25 | 大连理工大学 | High-precision rotating blade vibration measurement method based on blade tip timing technology |
| CN112179480A (en) * | 2020-08-26 | 2021-01-05 | 西安交通大学 | Method and system for identifying timing vibration parameters of harmonic superposition fitting blade tip and electronic equipment |
| CN112182802A (en) * | 2020-09-29 | 2021-01-05 | 上海交通大学 | Method for realizing optimized design of aeroelasticity of impeller machinery with random detuning |
| CN112733600A (en) * | 2020-12-03 | 2021-04-30 | 西安交通大学 | Blade fault diagnosis method without rotating speed reference signal |
| CN114450564A (en) * | 2019-10-28 | 2022-05-06 | 三菱重工业株式会社 | Detection device, rotating equipment and detection method |
| CN114608773A (en) * | 2022-01-25 | 2022-06-10 | 大连理工大学 | Blade high-order synchronous vibration parameter identification method based on double-parameter method |
| CN114674412A (en) * | 2022-03-17 | 2022-06-28 | 大连理工大学 | Blade tip timing measurement method without rotating speed synchronous signal |
| CN115420506A (en) * | 2022-09-08 | 2022-12-02 | 浙江海骆航空科技有限公司 | High-speed rotating blade explosion flying-off phase control test device and method |
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| CN110307894A (en) * | 2019-07-12 | 2019-10-08 | 天津大学 | Based on the shrouded blade vibration measuring method and calibration system for improving Tip-Timing principle |
| CN110307894B (en) * | 2019-07-12 | 2024-05-10 | 天津大学 | Vibration measuring method and calibration system for shrouded blade based on improved blade tip timing principle |
| CN110851963A (en) * | 2019-10-25 | 2020-02-28 | 西安交通大学 | Casing circumferential arrangement method of blade end timing sensor |
| CN114450564A (en) * | 2019-10-28 | 2022-05-06 | 三菱重工业株式会社 | Detection device, rotating equipment and detection method |
| CN114450564B (en) * | 2019-10-28 | 2024-04-30 | 三菱重工业株式会社 | Detection device, rotation apparatus, and detection method |
| CN111323190A (en) * | 2020-04-13 | 2020-06-23 | 北京化工大学 | Measuring method and measuring device for five-dimensional vibration of rotating blade |
| CN111323190B (en) * | 2020-04-13 | 2021-01-12 | 北京化工大学 | Measuring method and measuring device for five-dimensional vibration of rotating blade |
| CN111579060A (en) * | 2020-06-28 | 2020-08-25 | 大连理工大学 | High-precision rotating blade vibration measurement method based on blade tip timing technology |
| CN111579060B (en) * | 2020-06-28 | 2021-09-24 | 大连理工大学 | High-precision rotating blade vibration measurement method based on blade tip timing technology |
| CN112179480A (en) * | 2020-08-26 | 2021-01-05 | 西安交通大学 | Method and system for identifying timing vibration parameters of harmonic superposition fitting blade tip and electronic equipment |
| CN112182802B (en) * | 2020-09-29 | 2021-10-19 | 上海交通大学 | Method for realizing optimized design of aeroelasticity of impeller machinery with random detuning |
| CN112182802A (en) * | 2020-09-29 | 2021-01-05 | 上海交通大学 | Method for realizing optimized design of aeroelasticity of impeller machinery with random detuning |
| CN112733600A (en) * | 2020-12-03 | 2021-04-30 | 西安交通大学 | Blade fault diagnosis method without rotating speed reference signal |
| CN114608773A (en) * | 2022-01-25 | 2022-06-10 | 大连理工大学 | Blade high-order synchronous vibration parameter identification method based on double-parameter method |
| CN114608773B (en) * | 2022-01-25 | 2022-11-29 | 大连理工大学 | Blade high-order synchronous vibration parameter identification method based on double-parameter method |
| CN114674412A (en) * | 2022-03-17 | 2022-06-28 | 大连理工大学 | Blade tip timing measurement method without rotating speed synchronous signal |
| CN115420506A (en) * | 2022-09-08 | 2022-12-02 | 浙江海骆航空科技有限公司 | High-speed rotating blade explosion flying-off phase control test device and method |
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