CN1789942A - Flexible rotor holographic dynamic balancing method based on empirical mode decomposition - Google Patents

Abstract

The invention discloses a holographic dynamic balance method based on empirical modal breakdown flexible rotor, which is characterized by the following: resolving the data of rotor in the whole speed raising course through empirical modal breakdown advantage based on holographic spectrum information integral elementary and system theory; extracting the industrial frequency component; drawing the holographic baud graph; calculating the weight quality and orientation of different rotary speeds, especially near the weight information of critical rotary speed. The invention breaks through the limitation of traditional stable data and reduces the risk, which can reach the better balancing effect.

Description

Flex rotor holographic dynamic balance method based on the empirical modal decomposition

Technical field

The invention belongs to the rotor dynamic balancing technical field, belong to rotary machinery fault diagnosis and control field, particularly the flex rotor holographic dynamic balance method that decomposes based on empirical modal.

Background technology

Common flex rotor balance method has two big classes now: modal balancing method and influence coefficient method.The thought of modal balancing method is in the whole range of speeds of rotor, according to the orthogonality of mode, balances each rank mode, finally reaches the purpose of rotor balancing.

When utilizing the modal balancing method to do balance, balancing speed preferably is selected in from the closer place of critical rotary speed, but, because its vibratory output is bigger near critical rotary speed, and traditional modal balancing method exactly requires to stop in the critical rotary speed vicinity and obtains steady state data, and this can bring very big balance risk to unit.In order to overcome the shortcoming of this traditional modal balancing method, proposed to have improved the flex rotor holographic dynamic balance method that decomposes based on empirical modal, it has utilized the thought of modal balancing method, but the transient data that only needs unit cycling start process, on the basis of 3D hologram spectral theory and empirical modal decomposition, obtain the counterweight information that each mode of balance will add.

" rotor holographic dynamic balance method " (referring to Chinese invention patent ZL97108694.X), " asymmetrical rotor holographic dynamic balance technology " (patent ZL00113755.7), " flex rotor low speed holographic dynamic balance method " (patent ZL03134387.2) are applied to dynamic balance field with holographic spectral technology and information theory principle respectively, by information integration, realized the holographic dynamic balance of symmetry and asymmetrical rotor and axle system.Above method has all realized the breakthrough of dynamic balancing technique aspect balance quality of rotor and balance efficiency two.In addition, empirical modal decomposes in following patent: Computer implemented empirical modedecomposition method, apparatus and article of manufacture (U.S.'s patent of invention 5983162), Computer implemented empirical mode decomposition method, apparatus, and article of manufacture for two-dimensional signals (U.S.'s patent of invention 6311130), Empirical mode decomposition apparatus, method and article ofmanufacture for analyzing biological signals and performing curve fitting (U.S.'s patent of invention 6381559), Computer implemented empirical mode decompositionmethod apparatus, and article of manufacture utilizing curvature extrema (U.S.'s patent of invention 6631325), Empirical mode decomposition apparatus, method andarticle of manufacture for analyzing biological signals and performing curvefitting (U.S.'s patent of invention 6738734), Three dimensional empirical modedecomposition analysis apparatus, among method and article manufacture (U.S.'s patent of invention 6782124) the Empirical mode decomposition for analyzing acoustical signals (U.S.'s patent of invention 6862558), obtain successful application at different fields, but also do not had relevant technology that it is applied in the transient equilibrium now.

Summary of the invention

The objective of the invention is to overcome the shortcoming of above-mentioned prior art, a kind of flex rotor holographic dynamic balance method that decomposes based on empirical modal has been proposed, on the basis that empirical modal decomposes, calculate near the different critical rotating speed counterweight information with the transient data of unit cycling start process, reduced the balance risk, reach the purpose of modal balancing method, simplified the transient equilibrium process.

Realize that technical solution of the present invention is: comprise two-dimension holographic spectrum and the 3D hologram spectrum of rotor under different rotating speeds of making the cross section with holographic spectral technology; First phase point with the power frequency ellipse characterizes the vibration that rotor is respectively measured the cross section;

Carry out as follows:

1) whole cycling start process current vortex sensor is surveyed rotor oscillation data and key signal before the record unit test mass, after vibration data carried out low-pass filtering, decompose this data with empirical mode decomposition method, obtain a plurality of intrinsic mode functions, first intrinsic mode function promptly is its power frequency component, the peak of adjacent two pulses of key signal, as the time interval, intercept the vibration data of gathering simultaneously with key signal by this time interval, organize the intercepting of adjacent pulse by boosting velocity procedure more, obtain the vibration data that the rotor one under the different rotating speeds changes, according to holographic spectral technology, draw rotor different cross section before the test mass under balancing speed the 3D hologram spectrum and the holographic Bode diagram of cycling start, comprise amplitude figure and phase diagram, balancing speed is got the 85%-90% of critical rotary speed;

2) with the vibration signal of cycling start before the rotor test mass, the power and the couple component that are made at balancing speed 3D hologram spectrum by following formula decompose, and balancing speed is got the 85%-90% of critical rotary speed;

${\stackrel{\→}{R}}_{\mathrm{Af}}={\stackrel{\→}{R}}_{\mathrm{Bf}}=0.5({\stackrel{\→}{R}}_A+{\stackrel{\→}{R}}_B)$ (1)

${\stackrel{\→}{R}}_{\mathrm{Ac}}=-{\stackrel{\→}{R}}_{\mathrm{Bc}}=0.5({\stackrel{\→}{R}}_A-{\stackrel{\→}{R}}_B)$

Represent the unbalance response in A and two cross sections of B,

With

Represent the force unbalance response in A and two cross sections of B, Represent the couple unbalance response component in A and two cross sections of B;

3) according to the orientation and the hysteresis horn cupping of the original vibration first phase point of unit, uneven test mass is added in examination on balanced surface;

4) the whole current vortex sensor after the additional examination of record unit weighs is surveyed rotor oscillation data and key signal, adopt then with step 1) in identical disposal route, extract power frequency modal components wherein, by holographic spectral technology, draw rotor different cross section before the test mass under balancing speed the 3D hologram spectrum and the holographic Bode diagram of cycling start, comprise amplitude figure and phase diagram, balancing speed is got the 85%-90% of critical rotary speed;

5) organize the derivatives at interval between the adjacent pulse peaks before the test mass in the key signal as a plurality of rotating speeds in the rotor boosting velocity procedure more, organize the derivatives at interval between the adjacent pulse peaks behind the test mass in the key signal as a plurality of rotating speeds in the rotor boosting velocity procedure more, obtain identical rotating speed in these two processes, again by the time period between two adjacent key phases pulse of same rotational speed correspondence as the time interval, intercept the vibration data of rotor with this time interval, obtain the vibration data that rotor one changes, the vibration data that rotor one changes behind the test mass deducts the vibration data of the last commentaries on classics of test mass, obtain the data that rotor one changes pure test mass, by holographic spectral technology, draw rotor different cross section before the test mass under balancing speed the 3D hologram spectrum and the holographic Bode diagram of cycling start, comprise amplitude figure and phase diagram, balancing speed is got the 85%-90% of critical rotary speed;

6) making power and the couple that 3D hologram is composed under the pure test mass according to formula (1) decomposes, and holographic Bode diagram, the corresponding single order modal response of force component, the corresponding second-order modal response of couple component, according to the orthogonality principle of the vibration shape, the force component of test mass only causes the single order vibration of rotor, and the couple component of test mass only causes the second order vibration of rotor, calculate under different rotating speeds the static(al) component of test mass and couple component according to following formula;

${\stackrel{\→}{I}}_f={\stackrel{\→}{A}}_{\mathrm{Tf}}-{\stackrel{\→}{A}}_{\mathrm{Of}}$ (2)

${\stackrel{\→}{I}}_c={\stackrel{\→}{A}}_{\mathrm{Tc}}-{\stackrel{\→}{A}}_{\mathrm{Oc}}$

With

Be the static(al) component and the couple component of test mass, Be the force component of test mass, Be the force component of original vibration,

Be the couple component of test mass, It is the couple component of original vibration.

7) according to the original unbalance response of each measurement face, the following formula of foundation calculates the fair-sized and the phase place of counterweight under balancing speed, and balancing speed is got the 85%-90% of critical rotary speed;

${\stackrel{\→}{P}}_{\mathrm{Af}}={\stackrel{\→}{P}}_{\mathrm{Bf}}=-{\stackrel{\→}{T}}_{\mathrm{Af}}\·\frac{{\stackrel{\→}{A}}_{\mathrm{Of}}}{{\stackrel{\→}{I}}_f}$ (3)

${\stackrel{\→}{P}}_{\mathrm{Ac}}=-{\stackrel{\→}{P}}_{\mathrm{Bc}}=-{\stackrel{\→}{T}}_{\mathrm{Ac}}\·\frac{{\stackrel{\→}{A}}_{\mathrm{Oc}}}{{\stackrel{\→}{I}}_c}$

Wherein, With Be the force component and the couple component of A cross section counterweight,

With Be the force component and the couple component of B cross section counterweight, With Be force component and the couple component of test mass in the A cross section, With

Be the force component and the couple component of original vibration, With Be the static(al) component and the couple component of test mass;

8) add counterweight after, the cycling start process of test unit, if satisfy the balance requirement, promptly unit can be broken through critical rotary speed smoothly, and under rated speed its magnitude of vibrations within the scope of unit nominal then balance finish; Otherwise, repeat above-mentioned steps.

The present invention is decomposed into the basis with holographic spectrum information integration principle and empirical modal, on the basis that obtains all sensors vibration information on the rotor, the amplitude-frequency phase information of integrated each supporting place vibration, the vibration behavior of different rotating speeds lower rotor part is described in the mode of 3D hologram spectrum and holographic Bode diagram comprehensively, obtain near the information of flex rotor its different critical rotating speed, and, realize the modal balancing method of flex rotor on this basis with this foundation as balance.

Characteristics of the present invention are as follows:

1. be decomposed into the basis with 3D hologram analysis of spectrum and empirical modal, merged the multidirectional vibration information of rotor, improved balance quality, fully taken into account rotor-bearing system, adopted the first phase point that changes the frequency ellipse to characterize magnitude of vibrations and the orientation that rotor is respectively measured the cross section respectively to the equal factor of rigidity.

2. utilize the thought of modal balancing method, but only needed the transient data of unit cycling start process, avoided traditional modal balancing method near critical rotary speed, to stop the shortcoming of obtaining steady state data, reduced the balance risk.

3. with the power and the couple decomposition method of holographic spectral technology and vibratory response, obtained near the balancing information of the flex rotor different critical rotating speed, with this reliable basis as the balance flex rotor.

4. counterweight meets the oval rule of phase shift, promptly with the minute surface symmetric relation between formed ellipse of original vibration and the formed oval 2 first phase points of counterweight, as the theoretical foundation of seeking the optimum balance scheme.

5. adopt two planes to increase the weight of simultaneously, test mass cycling start once or twice can realize the balance of each rank mode of flex rotor in the whole range of speeds, and has reduced the balance risk that traditional modal balancing method requirement is brought in the stop of critical rotary speed place.

Description of drawings

Fig. 1 (a) is that angle compensation of the present invention calculates synoptic diagram;

Fig. 1 (b) is a rotor rotation synoptic diagram;

Fig. 2 is the experiment table arrangenent diagram,

Fig. 2 (a) is a vertical axial experiment table synoptic diagram;

Fig. 2 (b) is a horizontal axis experiment table synoptic diagram;

Fig. 3 is a balance process flow diagram of the present invention;

Fig. 4 is the 3D hologram spectral factorization figure of original vibration under the 2001RPM;

Fig. 4 (a) is the 3D hologram spectrogram of original vibration under the 2001RPM;

Wherein, horizontal ordinate is the displacement of directions X, and unit is V (volt), and ordinate is the displacement of Y direction, and unit is V;

Fig. 4 (b) is the force component figure of original vibration 3D hologram spectral factorization under the 2001RPM;

Wherein, horizontal ordinate is the displacement of directions X, and unit is V, and ordinate is the displacement of Y direction, and unit is V;

Fig. 4 (c) is that the couple of original vibration 3D hologram spectral factorization under the 2001RPM is divided spirogram;

Wherein, horizontal ordinate is the displacement of directions X, and unit is V, and ordinate is the displacement of Y direction, and unit is V;

Fig. 5 is the holographic Bode diagram in rotor raising speed A cross section before the test mass:

Fig. 5 (a) is the holographic baud amplitude figure in rotor raising speed A cross section before the test mass;

Fig. 5 (b) is the first phase point phase diagram in rotor raising speed A cross section before the test mass;

Fig. 6 is the holographic Bode diagram in rotor raising speed B cross section before the test mass:

Fig. 6 (a) is the holographic baud amplitude figure in rotor raising speed B cross section before the test mass;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an amplitude, and unit is V;

Fig. 6 (b) is the first phase point phase diagram in rotor raising speed B cross section before the test mass;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an angle, and unit is degree.

Fig. 7 is the holographic Bode diagram in rotor raising speed A cross section behind the test mass:

Fig. 7 (a) is the holographic baud amplitude figure in rotor raising speed A cross section behind the test mass;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an amplitude, and unit is V;

Fig. 7 (b) is the first phase point phase diagram in rotor raising speed A cross section behind the test mass;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an angle, and unit is degree.

Fig. 8 is the holographic Bode diagram in rotor raising speed B cross section behind the test mass:

Fig. 8 (a) is the holographic baud amplitude figure in rotor raising speed B cross section behind the test mass;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an amplitude, and unit is V;

Fig. 8 (b) is the first phase point phase diagram in rotor raising speed B cross section behind the test mass;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an angle, and unit is degree.

Fig. 9 is the holographic Bode diagram in pure test mass A cross section:

Fig. 9 (a) is the holographic baud amplitude figure in pure test mass A cross section;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an amplitude, and unit is V;

Fig. 9 (b) is the first phase point phase diagram in pure test mass A cross section;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an angle, and unit is degree.

Figure 10 is the holographic Bode diagram in pure test mass B cross section:

Figure 10 (a) is the holographic baud amplitude figure in pure test mass B cross section;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an amplitude, and unit is V;

Figure 10 (b) is the first phase point phase diagram in pure test mass B cross section;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an angle, and unit is degree.

Figure 11 (a) is the 3D hologram spectrogram of pure test mass under the 2001RPM;

Wherein, horizontal ordinate is the displacement of directions X, and unit is V, and ordinate is the displacement of Y direction, and unit is V;

Figure 11 (b) is the force component figure of pure test mass 3D hologram spectral factorization under the 2001RPM;

Wherein, horizontal ordinate is the displacement of directions X, and unit is V, and ordinate is the displacement of Y direction, and unit is V;

Figure 11 (c) is that the couple of pure test mass 3D hologram spectral factorization under the 2001RPM is divided spirogram;

Wherein, horizontal ordinate is the displacement of directions X, and unit is V, and ordinate is the displacement of Y direction, and unit is V;

Figure 12 is the comparison diagram of Bode diagram (amplitude figure) before and after the balance;

Figure 12 (a) is the Bode diagram in A cross section before the balance;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an amplitude, and unit is V;

Figure 12 (b) is the Bode diagram in A cross section after the balance;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an amplitude, and unit is V;

Figure 12 (c) is the Bode diagram in B cross section before the balance;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an amplitude, and unit is V;

Figure 12 (d) is the Bode diagram in B cross section after the balance;

Horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an amplitude, and unit is V.

Below in conjunction with accompanying drawing content of the present invention is described in further detail.

Embodiment

The present invention at first gathers fault unit data, utilize holographic spectral technology to make a definite diagnosis the fault type that unit is in operation, the commentaries on classics frequency fault of rotor imbalance and other type is correctly made a distinction, if unit is to take fault as the leading factor with imbalance, then, select balanced surface according to the vibration situation and the field balancing condition of fault machine group rotor.

Shown in Fig. 1 (a) and (b), wherein (a) expression is if move past the δ angle with first phase point changeing on the frequency ellipse, and then the rotor test mass moves past the ω angle, generally speaking, and δ ≠ ω.Wherein, φ is an offset angle.Figure (b) is rotor rotation synoptic diagram, and wherein ω is the angle of rotor rotation.

Shown in Fig. 2 (a) and (b), 1,2 are two current vortex sensors that measurement axis is shaken near each 45 ° of layout about the A bearing among Fig. 2 (a); 3,4 are two current vortex sensors that measurement axis is shaken near each 45 ° of layout about the B bearing; 5 are arranged horizontally the current vortex sensor of measuring key signal; C, D are two and increase the weight of dish; A, B represent bearing.To the rotor free end, rotor counterclockwise rotates from motor side, passes through the Y direction sensor again through the directions X sensor earlier.Test mass on the rotating disk increases the weight of the angle, by calculating from the counterclockwise rotation direction of keyway.Scheming (b) is and shaft parallel direction sensor distribution schematic diagram, and number of sensor is identical with figure (a), and wherein, Ω is a gyro frequency.

With reference to shown in Figure 3, the implication that wherein meets representative is as follows, selected rotating speed when W--is used for modal balancing, and it is more approaching with corresponding critical rotary speed;

A, the original unbalance response of B two measurement faces under rotating speed W that a, b--characterize with holographic spectrum first phase point vector;

A _b, P _b--amplitude figure and phase diagram before the test mass in the rotor holographic Bode diagram;

A _a, p _a--amplitude figure and phase diagram behind the test mass in the rotor holographic Bode diagram;

A _d, P _d--amplitude figure and phase diagram in the rotor holographic Bode diagram of pure test mass;

a _F0, b _F0--original unbalance response a, b under the rotating speed W decompose resulting force unbalance response by holographic spectrum power and couple;

a _C0, b _C0--original unbalance response a, b under the rotating speed W decompose resulting couple unbalance response by holographic spectrum power and couple;

a _Ft, b _Ft--under the rotating speed W, the force unbalance that is caused by pure test mass that obtains by holographic spectral factorization responds;

a _Ct, b _Ct--under the rotating speed W, the couple unbalance that is caused by pure test mass that obtains by holographic spectral factorization responds;

i _Ft, i _Ct--under the rotating speed W, by caused unit force of pure test mass and couple unbalance response;

P _f, P _c--under the rotating speed W, should add the power and the couple component of counterweight;

P ₁, P ₂--under the rotating speed W, C, the counterweight on D two sides.

The implementation process of Fig. 3 representative is as follows:

1) near the whole cycling start process of unit before the collection test mass, and the data the intercepting critical rotary speed is carried out the empirical modal decomposition, extracts power frequency mode wherein, draws out holographic Bode diagram, comprises amplitude figure A _bWith phase diagram P _b

2) data of a certain rotating speed W of extraction critical rotary speed near are carried out the 3D hologram spectral factorization of original signal, obtain the force component a under this rotating speed _F0, b _F0, couple component a _C0, b _C0

3) will record a and b under the rotating speed W as rotor ready to balance object;

4) add the test mass of 1g zero degree at the C balanced surface, add the test mass of 1g90 degree, the whole cycling start process of gathering unit again at the D balanced surface, and near the data the intercepting critical rotary speed are carried out the empirical modal decomposition, extract power frequency mode wherein, draw out holographic Bode diagram, comprise amplitude figure A _aWith phase diagram P _a

5) according to before the test mass and the holographic Bode diagram behind the test mass, calculate the holographic Bode diagram of pure test mass, comprise amplitude figure A _dWith phase diagram P _d

6) according to the holographic Bode diagram of pure test mass, extract the data of a certain rotating speed W critical rotary speed near, carry out the 3D hologram spectral factorization of pure test mass, obtain the force component a under this rotating speed _Ft, b _Ft, couple component a _Ft, b _Ft

7) utilize angle compensation and added test mass information, force-responsive i that can the unit's of calculating test mass _FtWith couple response i _Ct

8) calculate the force component that should add counterweight: P _f=a _F0/ i _FtCalculate the couple component that should add counterweight: P _c=a _C0/ i _Ct

9) the counterweight information after calculating is synthesized is at C balanced surface P ₁=P _f+ P _cAt D balanced surface P ₂=P _f-P _c

Shown in Fig. 4 (a) and (b), (c), the original vibration 3D hologram spectral factorization result who is obtained by formula (1) shows that based on force component, the couple component is very little in the original vibration.

With reference to Fig. 5 wherein (a) be amplitude figure, horizontal ordinate is a rotating speed, unit be RPM (rev/min), ordinate is an amplitude, and unit is V, and what the solid line among the figure was represented is the Bode diagram of directions X, what dotted line was represented is the Bode diagram of Y direction, what dotted line was represented is X and the synthetic Bode diagram of Y direction, if do not have under the situation of specified otherwise, the implication of various types of linear representatives is all identical in the following amplitude Bode diagram; (b) be first phase point phase diagram, horizontal ordinate is a rotating speed, and unit is RPM, and ordinate is an angle, and unit is degree.

Shown in Fig. 5 (a) and (b), there is bigger vibratory output in the A cross section of rotor-support-foundation system near critical rotary speed, and the phase place of first phase point the critical rotary speed annex taken place near 180 the degree upset.

With reference to Fig. 6 (a) (b) shown in, there is bigger vibratory output in the B cross section of rotor-support-foundation system near critical rotary speed, and the phase place of first phase point the critical rotary speed annex taken place near 180 the degree upset.

With reference to Fig. 7 (a) (b) shown in, add test mass after, still there is bigger vibratory output in the A cross section of rotor-support-foundation system near critical rotary speed, and the upset of spending near 180 has taken place at the critical rotary speed annex phase place of first phase point.

With reference to Fig. 8 (a) (b) shown in, add test mass after, still there is bigger vibratory output in the B cross section of rotor-support-foundation system near critical rotary speed, and the upset of spending near 180 has taken place at the critical rotary speed annex phase place of first phase point.

With reference to Fig. 9 (a) (b) shown in, according to before the test mass and test mass after holographic Bode diagram, calculate amplitude Bode diagram and the first phase point phase diagram of rotor-support-foundation system at the pure test mass in A cross section, can calculate the 3D hologram spectrum information in the A cross section under the corresponding rotating speed according to this figure;

With reference to Figure 10 (a) (b) shown in, according to before the test mass and test mass after holographic Bode diagram, calculate amplitude Bode diagram and the first phase point phase diagram of rotor-support-foundation system at the pure test mass in B cross section, can calculate the 3D hologram spectrum information in B cross section under the corresponding rotating speed according to this figure;

(b) shown in (c), the 3D hologram spectral factorization result who is obtained pure test mass under the 2001RPM by formula (1) shows that still based on force component, the couple component is very little in the pure test mass with reference to Figure 11 (a).

With reference to Figure 12 (a) (b) (c) (d) shown in, can know that by contrast after using this method rotor being carried out balance, the threshold vibration amplitude of rotor has been reduced greatly.

Balance target: adopt the improved flex rotor holographic dynamic balance method that decomposes based on empirical modal, reduce critical rotary speed (mainly being that single order is critical) the original imbalance of experiment table down.Testing table balance fine under working speed (critical), but the bigger vibratory output of the critical existence of single order greater than single order.

Its balance flow process of flex rotor holographic dynamic balance method based on empirical modal decomposes specifies as follows:

1. the whole cycling start process data before the record unit test mass is carried out empirical modal to data and is decomposed, and extracts power frequency modal components wherein, draws out the holographic Bode diagram of the preceding cycling start of test mass, comprises amplitude figure and and phase diagram.Fig. 5 and Fig. 6 are the holographic Bode diagram in the preceding A of test mass and two cross sections of B.The 3D hologram that utilizes formula (1) to draw out under the rotating speed 2001RPM (near critical) is composed and corresponding power and couple decomposition, as shown in Figure 4.

2. according to selected balanced surface,, determine to add the size and the orientation of uneven test mass according to the orientation and the hysteresis horn cupping of the original vibration first phase point of unit;

3. the test mass that adds 0 ° of 1g ∠ in the A cross section, the test mass that adds 90 ° of 1g ∠ in the B cross section, whole cycling start process data after the additional examination of record unit is heavy, data are carried out empirical modal decomposes, extract power frequency modal components wherein, draw out the holographic Bode diagram that adds cycling start behind the test mass, comprise amplitude figure and and phase diagram.Fig. 7 and Fig. 8 are the holographic Bode diagram of A and two cross sections of B behind the test mass.

4. utilize the car data that rises before the test mass and behind the test mass, be made at the 3D hologram spectrum of pure test mass under the different rotating speeds, and the holographic Bode diagram of pure test mass, comprise amplitude figure and and phase diagram, utilize formula (1) to obtain the 3D hologram spectrum and the holographic Bode diagram of pure test mass under balancing speed.Be the A of pure test mass and the holographic Bode diagram in two cross sections of B as Fig. 9 and Figure 10, Figure 11 is the 3D hologram spectral factorization of pure test mass under near the 2001RPM critical rotary speed.

5. obtain corresponding data as shown in Table 1 according to above analysis

Table one (unit: V ∠ °)

The first phase point	Original vibration		Force component		The couple component
							The A face	The B face	The A face	The B face	The A face	The B face
	The original vibration of 2001RPM	0.485∠36.4	0.444∠42.2	0.456∠37.7	0.456∠37.7	0.038∠59.3							0.038∠239.3
The pure test mass response of 2001RPM							0.831∠347	0.889∠350	0.885∠341	0.885∠341	0.039∠184	0.039∠4

(annotate: all vibration vectors are the holography spectrum parameter-oval first phase point vector of commentaries on classics frequency after the holographic conversion)

6. behind the angle compensation, utilize formula (2) to obtain the response of unit test mass; Original vibration A face during with rotating speed 2001RPM: 36.4 ° of 0.485V ∠ and B face: 42.2 ° of 0.444V ∠ are as the balance object, principle by the phase shift ellipse, when test mass is added on the original uneven first phase point mirror image symmetric position, counterbalance effect the best is utilized the counterweight C face after formula (3) obtains to calculate: P ₁228 ° of=0.72g ∠; D face: P ₂330 ° of=0.42g ∠.

7. the result of calculation of foundation 6 adds corresponding counterweight, gathers the boosting velocity procedure of rotor once more, make corresponding Bode diagram, compare before the balance and the result after the balance, as shown in figure 12, as seen near the vibration of rotor critical rotary speed reduced greatly, and counterbalance effect is better.

Claims (1)

1. the flex rotor holographic dynamic balance method that decomposes based on empirical modal comprises two-dimension holographic spectrum and the 3D hologram spectrum of rotor under different rotating speeds of making the cross section with holographic spectral technology; First phase point with the power frequency ellipse characterizes the vibration that rotor is respectively measured the cross section;

It is characterized in that, carry out as follows:

1) whole cycling start process current vortex sensor is surveyed rotor oscillation data and key signal before the record unit test mass, after vibration data carried out low-pass filtering, decompose this data with empirical mode decomposition method, obtain a plurality of intrinsic mode functions, first intrinsic mode function promptly is its power frequency component, the peak of adjacent two pulses of key signal, as the time interval, intercept the vibration data of gathering simultaneously with key signal by this time interval, organize the intercepting of adjacent pulse by boosting velocity procedure more, obtain the vibration data that the rotor one under the different rotating speeds changes, according to holographic spectral technology, draw rotor different cross section before the test mass under balancing speed the 3D hologram spectrum and the holographic Bode diagram of cycling start, comprise amplitude figure and phase diagram, balancing speed is got the 85%-90% of critical rotary speed;

2) with the vibration signal of cycling start before the rotor test mass, the power and the couple component that are made at balancing speed 3D hologram spectrum by following formula decompose, and balancing speed is got the 85%-90% of critical rotary speed;

${\stackrel{\→}{R}}_{\mathrm{Af}}={\stackrel{\→}{R}}_{\mathrm{Bf}}=0.5({\stackrel{\→}{R}}_A+{\stackrel{\→}{R}}_B)---\left(1\right)$

${\stackrel{\→}{R}}_{\mathrm{Ac}}=-{\stackrel{\→}{R}}_{\mathrm{Bc}}=0.5({\stackrel{\→}{R}}_A-{\stackrel{\→}{R}}_B)$

Represent the unbalance response in A and two cross sections of B,

With

Represent the force unbalance response in A and two cross sections of B, Represent the couple unbalance response component in A and two cross sections of B;

3) according to the orientation and the hysteresis horn cupping of the original vibration first phase point of unit, uneven test mass is added in examination on balanced surface;

4) the whole current vortex sensor after the additional examination of record unit weighs is surveyed rotor oscillation data and key signal, adopt then with step 1) in identical disposal route, extract power frequency modal components wherein, by holographic spectral technology, draw rotor different cross section before the test mass under balancing speed the 3D hologram spectrum and the holographic Bode diagram of cycling start, comprise amplitude figure and phase diagram, balancing speed is got the 85%-90% of critical rotary speed;

5) organize the derivatives at interval between the adjacent pulse peaks before the test mass in the key signal as a plurality of rotating speeds in the rotor boosting velocity procedure more, organize the derivatives at interval between the adjacent pulse peaks behind the test mass in the key signal as a plurality of rotating speeds in the rotor boosting velocity procedure more, obtain identical rotating speed in these two processes, again by the time period between two adjacent key phases pulse of same rotational speed correspondence as the time interval, intercept the vibration data of rotor with this time interval, obtain the vibration data that rotor one changes, the vibration data that rotor one changes behind the test mass deducts the vibration data of the last commentaries on classics of test mass, obtain the data that rotor one changes pure test mass, by holographic spectral technology, draw rotor different cross section before the test mass under balancing speed the 3D hologram spectrum and the holographic Bode diagram of cycling start, comprise amplitude figure and phase diagram, balancing speed is got the 85%-90% of critical rotary speed;

6) making power and the couple that 3D hologram is composed under the pure test mass according to formula (1) decomposes, and holographic Bode diagram, the corresponding single order modal response of force component, the corresponding second-order modal response of couple component, according to the orthogonality principle of the vibration shape, the force component of test mass only causes the single order vibration of rotor, and the couple component of test mass only causes the second order vibration of rotor, calculate under different rotating speeds the static(al) component of test mass and couple component according to following formula;

${\stackrel{\→}{I}}_f={\stackrel{\→}{A}}_{\mathrm{Tf}}-{\stackrel{\→}{A}}_{\mathrm{Of}}$

${\stackrel{\→}{I}}_c={\stackrel{\→}{A}}_{\mathrm{Tc}}-{\stackrel{\→}{A}}_{\mathrm{Oc}}---\left(2\right)$

With

Be the static(al) component and the couple component of test mass, Be the force component of test mass, Be the force component of original vibration, Be the couple component of test mass, It is the couple component of original vibration.

7) according to the original unbalance response of each measurement face, the following formula of foundation calculates the fair-sized and the phase place of counterweight under balancing speed, and balancing speed is got the 85%-90% of critical rotary speed;

${\stackrel{\→}{P}}_{\mathrm{Af}}={\stackrel{\→}{P}}_{\mathrm{Bf}}=-{\stackrel{\→}{T}}_{\mathrm{Af}}\·\frac{{\stackrel{\→}{A}}_{\mathrm{Of}}}{{\stackrel{\→}{I}}_f}$

${\stackrel{\→}{P}}_{\mathrm{Ac}}=-{\stackrel{\→}{P}}_{\mathrm{Bc}}=-{\stackrel{\→}{T}}_{\mathrm{Ac}}\·\frac{{\stackrel{\→}{A}}_{\mathrm{Oc}}}{{\stackrel{\→}{I}}_c}---\left(3\right)$

Wherein,

With Be the force component and the couple component of A cross section counterweight, With Be the force component and the couple component of B cross section counterweight, With Be force component and the couple component of test mass in the A cross section, With

Be the force component and the couple component of original vibration, With Be the static(al) component and the couple component of test mass;

8) add counterweight after, the cycling start process of test unit, if satisfy the balance requirement, promptly unit can be broken through critical rotary speed smoothly, and under rated speed its magnitude of vibrations within the scope of unit nominal then balance finish; Otherwise, repeat above-mentioned steps.

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