CN102175394A - Permanent calibration method in soft bearing dynamic unbalance test of rigid rotor - Google Patents

Abstract

The invention discloses a permanent calibration method in soft bearing dynamic unbalance test of a rigid rotor, belonging to the technical field of mechanical measurement. The method can realize permanent system calibration on a soft bearing dynamic unbalance machine and is characterized in that inherent frequency of a vibrating system consisting of a support system and a detected rotor is calculated by acquiring rotary frequencies and amplitudes of the support system at the corresponding moments in the process of rotor acceleration, thereby characterizing the influence of the quality of the rotor on the vibrating amplitude of the rotor by mapping. The influence of the quality and the rotating speed (inertia force of the rotor) of the rotor on calibration is eliminated. The permanent system calibration on the soft bearing dynamic balance machine is realized.

Description

Permanent scaling method in the rigid rotator soft underprop unbalance dynamic test

Technical field

The present invention is the method in a kind of mechanical measurement technique field, is specifically related to the permanent scaling method in a kind of rigid rotator soft underprop unbalance dynamic test.

Background technology

Have now and mainly use influence coefficient method to carry out to the demarcation of soft underprop unbalance dynamic test macro, the result of demarcation is only for being applicable in the dynamic balance running identical with working speed with current Structural Parameters of its Rotor.If the rotor type during the unbalance dynamic test or the rotor type or the rotor structure of rotor structure and timing signal are inconsistent, the calibration result of system is inapplicable, does not promptly possess permanent calibration characteristic.

The Zhou Shiyan of BJ University of Aeronautics ﹠ Astronautics professor has spelt out the rotor unbalance dynamic in paper " solves the new way that rigid rotator left and right sides rectifying plane influences problem " measurement is subjected to measuring rotating speed, the influence of relevant amount such as Structural Parameters of its Rotor.The influence of rotor quality in the soft-bearing dynamic balance measuring system be can not ignore, and the permanent system scaling method that uses in the hard bearing dynamic balancing machine can not be applicable to the soft-bearing dynamic balance machine.

The Sheng Deen of Carl Schenck AG also spells out in " elimination of the hard bearing balan errors of principles and the conception of novel equilibrator " along with the increase of measuring rotating speed and natural frequency ratio, the quality of rotor itself and system damping band more and more be can not ignore the influence that measurement brings, and the method that is merely able to the demarcation of employing state in the thinking soft underprop system according to routine is finished the unbalance dynamic measurement of soft underprop system.And the coefficient that state is demarcated has and rotor type and the closely-related characteristic of working speed.

Mr. Sheng Deen is at its patent " dynamic balancing measurement method and high frequency are than hard supporting dynamic poise device " (publication number: CN1566914A simultaneously, the open date: adopted the method that characterizes rotor moment of inertia on January 19th, 2005), and then partly considered the influence of quality of rotor own and moment of inertia to dynamic balancing measurement, enlarged the frequency measurement scope of classical hard supporting balance.But its at be the measuring process of hard bearing balan.

Planar separation and system's mark that the Pan Shuan of Zhejiang University summer, oneself professor of Yankee measure unbalance dynamic in " dynamic balancing machine system error analysis and scaling method research " carried out detailed elaboration, influence coefficient method for the employing of soft underprop system, vector influence coefficient method and linear regression least square influence coefficient method are carried out system calibrating, these all are to be based upon improving one's methods on the basis that state demarcates, and can't realize permanent demarcation effect of demarcating in the similar hard supporting system.

Summary of the invention

The present invention is directed to the deficiency that above-mentioned prior art exists, permanent scaling method in a kind of rigid rotator soft underprop unbalance dynamic test is provided, can on soft underprop unbalance dynamic machine, realize the permanent system demarcation, by gathering the commentaries on classics frequency and the supporting system amplitude of going through in the rotor accelerator in the corresponding moment, calculate the natural frequency of the vibrational system of supporting system and measured rotor composition, and then mapping characterizes out the quality of rotor to the rotor oscillation effect on amplitude.Eliminate the influence of rotor quality and rotating speed (rotor inertial forces) to demarcating.Realize the permanent system demarcation of soft-bearing dynamic balance machine.

The present invention is achieved through the following technical solutions, and the present invention includes following steps:

The first step: the acceleration that detected rotor is carried out progressively drives, until high workload rotating speed, utilize speed pickup to obtain each gyro frequency in the rotor accelerator continuously, utilize vibration-measuring sensor to obtain the amplitude of the supporting rocker under the corresponding rotation frequency simultaneously, the gyro frequency that obtains after rotor arrives stabilized (steady-state) speed in the rotor full speed process is vibrated frequency and amplitude data one to one with the supporting rocker.

Second step: the rotational speed omega when the frequency and amplitude data that obtain according to the first step are obtained the peak swing of rotor before reaching resonance state _N-1And rotor breaks away from the amplitude limiting mechanism rotational speed omega in when restriction in accelerator _N+1, and with Natural frequency as the unbalance dynamic measuring system.

The 3rd step: rotor quality is expressed as

Wherein: K is system constants, ω _nBe natural frequency; K can determine ω in the system calibrating process _nFor obtaining the result after the rapid execution of previous step.

The 4th step: carry out system calibrating, and obtain the system calibrating coefficient

Be specially:

$\left[\begin{array}{cc}x1\·\mathrm{ro}\stackrel{\→}{u}11& x2\·\mathrm{ro}\stackrel{\→}{u}21\\ x3\·\mathrm{ro}\stackrel{\→}{u}12& x4\·\mathrm{ro}\stackrel{\→}{u}22\end{array}\right]\left[\begin{array}{c}\stackrel{\→}{m}1\\ \stackrel{\→}{m}2\end{array}\right]=\left[\begin{array}{c}\stackrel{\→}{U}1\\ \stackrel{\→}{U}2\end{array}\right],$ Wherein:

$x_1=\frac{{\mathrm{\&omega;}}^2{r}_1(b+c)}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_{\mathrm{<figure-callout\; id="2"\; label="n"\; filenames="HDA0000046297940000013.png,HDA0000046297940000021.png"\; state="\{\{state\}\}">n</figure-callout>}}^2}+1)},$ $x_2=\frac{{\mathrm{\&omega;}}^2{r}_{2}c}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_{\mathrm{<figure-callout\; id="2"\; label="n"\; filenames="HDA0000046297940000013.png,HDA0000046297940000021.png"\; state="\{\{state\}\}">n</figure-callout>}}^2}+1)}.$

$x_3=\frac{{\mathrm{\&omega;}}^2{r}_{1}a}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_{\mathrm{<figure-callout\; id="2"\; label="n"\; filenames="HDA0000046297940000013.png,HDA0000046297940000021.png"\; state="\{\{state\}\}">n</figure-callout>}}^2}+1)},$ $x_2=\frac{{\mathrm{\&omega;}}^2{r}_2(a+b)}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_{\mathrm{<figure-callout\; id="2"\; label="n"\; filenames="HDA0000046297940000013.png,HDA0000046297940000021.png"\; state="\{\{state\}\}">n</figure-callout>}}^2}+1)},$

The 5th step: rotor is done vibration in the plane of oscillation, arrive according to the pick-up sensor

With , obtain unbalance mass, on the corresponding rectifying plane according to the planar separation equation

Be specially:

Wherein:

Be the equivalent unbalance mass, on the corresponding rectifying plane,

With

Be the vibratory output of the supporting rocker of sensor, K is the rigidity of the single supporting of supporting rocker, ω _nBe that supporting rocker and rotor form the natural frequency of vibrational system, ω is the rotor rotation angular velocity in the steady state measurement process, and a be the left rectifying plane distance of left side supporting distance, b be left rectifying plane apart from right rectifying plane distance, c is that right rectifying plane is apart from right length of support, r ₁Be left rectifying plane amount of unbalance position, r ₂Be right rectifying plane amount of unbalance position.

Compared with prior art, the invention has the beneficial effects as follows the permanent demarcation that has realized the soft-bearing dynamic balance machine.Through asking for of the above-mentioned natural frequency of supporting system and rotor being formed system, and row are write the planar separation equation of dynamic balancing measurement again, can realize the permanent demarcation of the dynamic-balance measuring system under the soft underprop system, make the calibration result of system be independent of the structural parameters of rotor itself, thereby the permanent demarcation of the system of realization, the stated accuracy of raising system and the efficient of dynamic balancing measurement reduce the technical requirement to the site operation personnel.Realize of the easy demarcation of soft-bearing dynamic balance machine as hard bearing balan.

Description of drawings

Fig. 1 be embodiment rotor rotational frequency with vibration amplitude between corresponding change curve.

Fig. 2 is the frequency range section of embodiment rotor gyro frequency and vibration amplitude.

Fig. 3 arranges synoptic diagram for embodiment;

Fig. 4 is the examples measure structural representation;

Among the figure: 1 supporting rocker, 2 supporting rockers, 3 amplitude limiting mechanisms, 4 pick-up sensors, 5 speed probes.

Embodiment

Below embodiments of the invention are elaborated, present embodiment is being to implement under the prerequisite with the technical solution of the present invention, provided detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.

As shown in Figure 3, present embodiment may further comprise the steps:

The first step, in order to obtain the parameter of rotor accelerator finer and smoothlyer, equilibrator adopts the servomotor with pre-set velocity and acceleration function that rotor is driven, and just start the locking device of supporting rocker system when at utmost reaching resonance state (peak swing) near rotor, through after the resonant frequency point, discharge the locking device of supporting rocker at once.

Second step, in the accelerator of rotor, uniformly-spaced gather vibration signal by vibration-measuring sensor, note corresponding rotor gyro frequency constantly simultaneously.Depict the frequency-amplitude curve of rotor, seek two moment point that amplitude equates before and after locking device locking, obtain the natural frequency of supporting and rotor set assembly system

Simultaneously according to expression formula Characterize out the quality of rotor.

The 3rd step, adopt the verification rotor that it is carried out accurate system calibrating, according to following mode measuring system is demarcated, can obtain the calibration coefficient of system

And record in the permanent memory body of equilibrator:

$\left[\begin{array}{cc}x1\&CenterDot;\mathrm{ro}\stackrel{\&RightArrow;}{u}11& x2\&CenterDot;\mathrm{ro}\stackrel{\&RightArrow;}{u}21\\ x3\&CenterDot;\mathrm{ro}\stackrel{\&RightArrow;}{u}12& x4\&CenterDot;\mathrm{ro}\stackrel{\&RightArrow;}{u}22\end{array}\right]\left[\begin{array}{c}\stackrel{\&RightArrow;}{m}1\\ \stackrel{\&RightArrow;}{m}2\end{array}\right]=\left[\begin{array}{c}\stackrel{\&RightArrow;}{U}1\\ \stackrel{\&RightArrow;}{U}2\end{array}\right],$ Wherein:

$x_1=\frac{{\mathrm{\&omega;}}^2{r}_1(b+c)}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_{\mathrm{<figure-callout\; id="2"\; label="n"\; filenames="HDA0000046297940000013.png,HDA0000046297940000021.png"\; state="\{\{state\}\}">n</figure-callout>}}^2}+1)},$ $x_2=\frac{{\mathrm{\&omega;}}^2{r}_{2}c}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_{\mathrm{<figure-callout\; id="2"\; label="n"\; filenames="HDA0000046297940000013.png,HDA0000046297940000021.png"\; state="\{\{state\}\}">n</figure-callout>}}^2}+1)}.$

$x_3=\frac{{\mathrm{\&omega;}}^2{r}_{1}a}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_{\mathrm{<figure-callout\; id="2"\; label="n"\; filenames="HDA0000046297940000013.png,HDA0000046297940000021.png"\; state="\{\{state\}\}">n</figure-callout>}}^2}+1)},$ $x_2=\frac{{\mathrm{\&omega;}}^2{r}_2(a+b)}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_{\mathrm{<figure-callout\; id="2"\; label="n"\; filenames="HDA0000046297940000013.png,HDA0000046297940000021.png"\; state="\{\{state\}\}">n</figure-callout>}}^2}+1)},$

The 4th step in the test process that carries out unbalancing value, still needed to try to achieve the natural frequency of respective rotor and supporting system, then by means of the calibration coefficient of having preserved in following and the system

Calculate in such a way

Obtain the unbalance mass, in the corresponding correcting plane:

Wherein: Be the equivalent unbalance mass, on the corresponding rectifying plane,

With

Be the vibratory output of the supporting rocker of sensor, K is the rigidity of the single supporting of supporting rocker, ω _nBe that supporting rocker and rotor form the natural frequency of vibrational system, ω is the rotor rotation angular velocity in the steady state measurement process, and a be the left rectifying plane distance of left side supporting distance, b be left rectifying plane apart from right rectifying plane distance, c is that right rectifying plane is apart from right length of support, r ₁Be left rectifying plane amount of unbalance position, r ₂Be right rectifying plane amount of unbalance position.

As shown in Figure 1, measured rotor is in the overall process of quickening, and the vibratory output of supporting rocker and the phase-shift phase of vibration signal are with measuring change in rotational speed trend.Its vibratory output reaches resonance for increasing earlier, is decreased to m ρ/M more gradually.Zhen Dong initial phase increases to π from zero simultaneously.And when rotor reaches resonance, that is to say when the rotor oscillation amount reaches maximum that the initial phase of rotor oscillation is a pi/2.

As shown in Figure 2, rotor quickens along heavy line among the figure in accelerator, until reaching the measurement rotating speed.Be respectively ω in both sides near resonance state _N-1, ω _N+1

As shown in Figure 3, rotor is subjected to the restriction of amplitude limiting mechanism in the process of quickening whirling vibration.Can't accurately detect the resonant frequency of rotor, so the next equivalent resonant frequency of average of the frequency in the moment of losing efficacy in the moment that the employing amplitude limiting mechanism works and process resonance back.

As shown in Figure 4, the dynamic balancing measurement of rotor relies on a speed pickup and two pick-up sensors to carry out the detection of rotor oscillation amount.

Permanent scaling method in the related soft-bearing dynamic balance machine of this method, comprise gyro frequency in the rotor accelerator and vibration amplitude are carried out equal interval sampling, obtain rotor and the natural frequency that supports rocker composition system according to sensor characteristic after the sampling, realize Function Mapping according to natural frequency, and finally realize permanent system calibration principle and method in the soft underprop balance test system rotor quality.Comprise to expansion on the rotor driven mode and application amplitude locking mode or do not lock the expansion of situation simultaneously.

This method be specially adapted to high precision soft-bearing dynamic balance test macro calibration process, can improve the calibration process of the equilibrator of various soft underprop system, realize permanent the demarcation, the complexity and the loaded down with trivial details property that need demarcation repeatedly when avoiding rotor type and structural change realize once forever demarcating.

Claims (1)

1. the permanent scaling method during a rigid rotator soft underprop unbalance dynamic is tested is characterized in that, may further comprise the steps:

The first step: the acceleration that detected rotor is carried out progressively drives, until high workload rotating speed, utilize speed pickup to obtain each gyro frequency in the rotor accelerator continuously, utilize vibration-measuring sensor to obtain the amplitude of the supporting rocker under the corresponding rotation frequency simultaneously, the gyro frequency that obtains after rotor arrives stabilized (steady-state) speed in the rotor full speed process is vibrated frequency and amplitude data one to one with the supporting rocker;

Second step: the rotational speed omega when the frequency and amplitude data that obtain according to the first step are obtained the peak swing of rotor before reaching resonance state _N-1And rotor breaks away from the amplitude limiting mechanism rotational speed omega in when restriction in accelerator _N+1, and with Natural frequency as the unbalance dynamic measuring system;

The 3rd step: rotor quality is expressed as

Wherein: K is system constants, ω _nBe natural frequency; K can determine ω in the system calibrating process _nFor obtaining the result after the rapid execution of previous step;

The 4th step: carry out system calibrating, and obtain the system calibrating coefficient Be specially:

$\left[\begin{array}{cc}x1\&CenterDot;\mathrm{ro}\stackrel{\&RightArrow;}{u}11& x2\&CenterDot;\mathrm{ro}\stackrel{\&RightArrow;}{u}21\\ x3\&CenterDot;\mathrm{ro}\stackrel{\&RightArrow;}{u}12& x4\&CenterDot;\mathrm{ro}\stackrel{\&RightArrow;}{u}22\end{array}\right]\left[\begin{array}{c}\stackrel{\&RightArrow;}{m}1\\ \stackrel{\&RightArrow;}{m}2\end{array}\right]=\left[\begin{array}{c}\stackrel{\&RightArrow;}{U}1\\ \stackrel{\&RightArrow;}{U}2\end{array}\right],$ Wherein:

$x_1=\frac{{\mathrm{\&omega;}}^2{r}_1(b+c)}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_n^2}+1)},$ $x_2=\frac{{\mathrm{\&omega;}}^2{r}_{2}c}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_n^2}+1)};$

$x_3=\frac{{\mathrm{\&omega;}}^2{r}_{1}a}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_n^2}+1)},$ $x_2=\frac{{\mathrm{\&omega;}}^2{r}_2(a+b)}{(a+b+c)(\frac{{\mathrm{\&omega;}}^2}{2{\mathrm{\&omega;}}_n^2}+1)},$

The 5th step: rotor is done vibration in the plane of oscillation, arrive according to the pick-up sensor With , obtain unbalance mass, on the corresponding rectifying plane according to the planar separation equation

Be specially:

Wherein:

Be the equivalent unbalance mass, on the corresponding rectifying plane, With

Be the vibratory output of the supporting rocker of sensor, K is the rigidity of the single supporting of supporting rocker, ω _nBe that supporting rocker and rotor form the natural frequency of vibrational system, ω is the rotor rotation angular velocity in the steady state measurement process, and a be the left rectifying plane distance of left side supporting distance, b be left rectifying plane apart from right rectifying plane distance, c is that right rectifying plane is apart from right length of support, r ₁Be left rectifying plane amount of unbalance position, r ₂Be right rectifying plane amount of unbalance position.

Images