RU2499985C1 - Rotor balancing method in one correction plane - Google Patents

Abstract

FIELD: machine building.

SUBSTANCE: rotor is installed in supports of balancing stand. There are two correction planes on rotor butt-ends, one of the planes is balancing and the other is testing. The rotor has specified maximum allowable asymmetry parameters - values of transverse displacement of masses centre and displacement angle of longitudinal principal axis of inertia at centre of gravity relative to its geometric axis. Rotor rotation is started, during rotation at first amplitudes and phases of vibration of both supports, induced by initial imbalances of rotor, are determined. Then, attaching test weights to each correction planes in sequence, amplitudes and phases of vibration of both supports are determined again. Then by the obtained results coefficients of balancing sensibility of the stand and coefficients of impact of correction planes are calculated. Then determined are values and angles of initial imbalances in each correction plane, used for determination of initial values of parameters of mass-inertial asymmetry. If at least one of these values exceeds specified admissible limit value, balancing imbalance is created in balancing correction plane. For its creation at first modelled is imbalance in balancing correction plane providing exclusion of initial imbalance in this correction plane, and then, considering coefficients of impact of correction planes, modelled is imbalance in balancing correction plane providing values of parameters of mass-inertial asymmetry not exceeding corresponding specified admissible limit values.

EFFECT: possibility of optimisation of parameters of mass-inertial asymmetry, improving accuracy of residual parameters of imbalance determination and reduction of labour intensity of balancing process.

3 cl, 5 dwg

Description

The invention relates to the field of dynamic balancing of rotors, namely, to control the parameters of mass-inertial asymmetry of the rotors and to ensure compliance of these parameters with the maximum permissible values, by changing the imbalance in one correction plane.

When assembling a high-speed vehicle made in the form of an axisymmetric rotor (cylinder, cone, truncated cone), it is often necessary not only to know the mass, position of the center of mass and moment of inertia of the rotor, but also to ensure the values specified in the operational documentation after its manufacture and assembly parameters of mass-inertial asymmetry, which include the value of the transverse displacement of the center of mass and the angle of deviation of the longitudinal main central axis of inertia (SCOI) relative to the geometric rotor axis. In this case, they strive primarily to minimize the transverse displacement of the center of mass, since its value significantly affects the stability of the vehicle around the center of mass.

The low accuracy of the theoretical calculation, the inevitable technological spread within certain limits of the characteristics of structural elements that are assembled inside the rotor (masses, moments of inertia, installation coordinates of elements and weights, due to the influence of random deviations of these characteristics from their calculated values), leads to the appearance of asymmetry in the mass distribution of the rotor, characterized by a skew of the longitudinal SCOI and a transverse displacement of the center of mass relative to the geometric axis of the rotor. This requires the use of experimental or computational-experimental methods for determining the indicated parameters of mass-inertial asymmetry in order to subsequently bring them with high accuracy to specified standards by adjusting the rotor mass. This problem arises in the layout of land, sea, air, space vehicles, the power plant of which is a complex rotor, which includes frames, compartments, sensor equipment, actuators. The solution to the problem of determining and bringing with high accuracy to the specified standards the parameters of mass-inertial asymmetry is the use of dynamic balancing stands with high instrumental accuracy, which provides a significant increase in the accuracy of determining these parameters compared with both theoretical calculation and experimental experimental data from the technical literature methods using devices that implement, for example, methods of static balancing, physical pendulum or a torsional oscillation.

As a rule, in the process of balancing the rotor in one correction plane, it is impossible to completely eliminate the main vector and the main moment of imbalances by combining the longitudinal GCI of the rotor with its geometric axis, so the task of the balancers is to achieve minimum and not exceeding the specified maximum permissible values of the transverse displacement of the center of mass and the angle of deviation longitudinal ГЦОИ from a geometrical axis of a rotor.

If during the balancing experiment it is revealed that the task of bringing simultaneously the two indicated parameters of the mass-inertial asymmetry of the controlled rotor to values not exceeding the specified maximum permissible values by loading the mass in one correction plane is impossible, the rotor is rejected and sent for re-arrangement.

A known method of single-plane balancing of the rotor [Fundamentals of balancing technology. T.1 // Ed. prof. V.A.Schepetilnikova. - M .: Mashinostroenie, 1975. P.184-186], which consists in the fact that a rotor having a correction plane is installed in the supports of the balancing stand, the rotor is rotated, first the amplitudes and phases of the support vibrations are measured, caused by the initial rotor unbalances, then the amplitudes and phases of the vibrations of the support are measured after attaching a test load to the correction plane, the mass and installation angle in the correction plane of the balancing weight are calculated from the results of these measurements.

In the process of balancing, the amplitudes and phases of the vibrations are measured for the support nearest to the correction plane. Based on the results obtained, the relative change in the vibration amplitude during rotation of the rotor with the test load and the phase angle of the vibration are determined, and the coefficient of the ratio of the balancing load to the test load, as well as the angle by which the balancing load should be moved from the place of installation of the test load, are found from these two values. Through the ratio and the weight of the test load, the mass of the balancing weight is found, and the angle of installation of the balancing weight is found from the values of the angular position of the test load and the angle of phase shift.

Simultaneous measurement of the amplitudes and phases of the vibration of the support can significantly reduce the balancing time of one plane of correction of the rotor, excluding analytically or using vector constructions of measurement errors of these parameters.

When balancing one plane of rotor correction, the method allows either static balancing with the elimination or reduction of the transverse displacement of the center of mass from the geometric axis of the rotor, or momentary balancing with the elimination or reduction of the deviation angle of the longitudinal rotary center for rotor, however, it does not provide simultaneous adjustment of the mass-inertial asymmetry of the rotor to values not exceeding the maximum permissible values.

There is a method of single-plane balancing of rotors, the imbalances of which are concentrated in one plane [Levit M.E., Ryzhenkov V.M. Balancing parts and assemblies. - M.: Mechanical Engineering, 1986. S. 71-76]. The method consists in installing a rotor having a correction plane in the supports of the balancing stand, turning the rotor in rotation, first measuring the amplitudes and phases of the support vibrations caused by the initial rotor imbalances, then measuring the amplitudes and phases of the support vibrations after attaching the test load to the correction plane, according to the results of these measurements, the mass and the installation angle are calculated in the plane of correction of the balancing load.

From the values of the amplitude and phase of vibration of one of the supports, the initial value and the angular position of the unbalance vector in the correction plane are found, the mass and the installation angle of the balancing weight are calculated, the attachment of which to the correction plane eliminates the effect of the initial imbalance in this plane and, thereby, eliminates the center offset rotor masses.

The disadvantage of this method is that when it is used, the problem of determining the main moment of imbalances and, consequently, the angle of deviation of the longitudinal center of the center from the geometric axis of the rotor is not solved, and therefore it is not possible to provide a given value of this parameter of the mass-inertial asymmetry of the rotor. The method is applicable only to rotors having the shape of a flat disk, the correction plane of which is located at an insignificant distance from the center of mass.

A known method of balancing the rotor in two planes [Levit M.E., Ryzhenkov V.M. Balancing parts and assemblies. - M.: Mechanical Engineering, 1986. P.76-77]. The method consists in the fact that a rotor is installed in the supports of the balancing stand, having two correction planes located at the ends and having known masses, distances from the center of mass to the correction planes, values of inertia moments, the rotor is rotated, first the amplitudes and phases of vibration of both supports are measured caused by the initial rotor imbalances, then, alternately attaching test weights to each of the correction planes, the amplitudes and phases of the vibrations of both supports are measured again, then the values and angles are determined vectors of initial imbalances in each correction plane.

The values and angular positions of the vectors of the initial imbalances calculate the masses and angular positions of the balancing weights for each correction plane, the installation of which in the corresponding correction plane will eliminate the initial imbalance.

As a result of eliminating the effect of the initial imbalances in both correction planes, the known method ensures the combination of the geometric axis and the longitudinal SCOI of the rotor, completely eliminating the lateral displacement of the center of mass and the angle of deviation of the longitudinal SCOI relative to the geometric axis of the rotor.

However, it requires not only a temporary installation of test weights, but also a permanent installation of balancing weights in two correction planes, which is not always possible.

A known method of balancing the rotor in one plane of correction [Journal: "Devices and systems. Management, Control, Diagnostics ”, authors: Klyuchnikov AV, Sidorov AV, article:“ Application of the method of low-frequency dynamic balancing for precision control of the parameters of mass-inertial asymmetry of rotor objects ”. - M .: Nauchtekhlitizdat, 2011, No. 3. S.48-53]. This method is adopted as a prototype as the closest in technical essence to the claimed method and has the most common essential features with the claimed method.

The known method consists in the fact that a rotor is installed in the supports of the balancing stand, with predetermined maximum permissible values of the transverse displacement of the center of mass and the angle of deviation of the longitudinal SCSI relative to its geometric axis, having two correction planes located at the ends, one of which is a balancing plane, and the other trial, and having known mass, distances from the center of mass to the correction planes, values of the moments of inertia, the rotor is rotated, during rotation, the amplitudes and phases are measured first The vibrations of both supports caused by the initial rotor imbalances, then, by attaching trial weights to each of the correction planes, the amplitudes and phases of the vibrations of both bearings are measured again, after which the coefficients of the balancing sensitivity of the bench and the coefficients of mutual influence of the correction planes are calculated, and then the values are determined and the angles of the vectors of initial imbalances in each correction plane, find the initial values of the transverse displacement of the center of mass relative to the geometric axis of the rotor and the angle of deviation of the longitudinal center for relative geometry of the rotor axis (mass-inertial asymmetry parameters), if at least one of them exceeds the specified maximum permissible value, create a balancing imbalance in the balancing correction plane, after calculating its value and angular position, after which determine the residual values of the parameters of mass inertial asymmetry, and then judge the balancing of the rotor by comparing the residual and maximum permissible values of the parameters associative-inertial asymmetry.

After calculating the value and the angular position of the balancing imbalance, according to the known laws of statics, the mass and angle of installation of the balancing load (s) are calculated, which ensures the creation of a balancing imbalance. Then set the balancing weight in the balancing plane of the correction of the rotor and re-control the values of the parameters of the residual mass-inertial asymmetry. The second control of the parameters is that the rotor is rotated, the amplitudes and phases of the vibrations of both supports are measured, and using the previously determined coefficients of the balancing sensitivity of the stand and the coefficients of mutual influence of the correction planes, the values of the residual unbalances acting in both correction planes are determined, by which the values of the residual mass inertial asymmetry parameters.

The method allows to achieve the maximum permissible values of the asymmetry parameters by setting the balancing weight (weights) in one plane of the rotor correction. The method is applicable in the case of using additional technological equipment for balancing the rotor.

The disadvantage of this method is that it does not simultaneously bring the values of both parameters of the mass-inertial asymmetry of the rotor to values not exceeding its maximum permissible values, which leads to an increase in the duration and complexity of the balancing experiment, due to the need to repeat the operations for calculating and installing balancing cargo, with subsequent control of the residual parameters of mass-inertial asymmetry. The need for multiple calculation and installation of balancing weights and experimental control of the parameters of residual mass-inertial asymmetry makes the method inconvenient for use in serial production of rotors.

The objective of the invention is to bring the values of both parameters of the mass-inertial asymmetry of the rotors to values not exceeding the specified maximum permissible values, and reducing the duration and complexity of the balancing process.

The technical result of the invention is the ability to optimize the parameters of mass-inertial asymmetry within their permissible values, less time-consuming control of the residual values of mass-inertial asymmetry by reducing the number of balancing operations and the accuracy of predicting the residual values of the parameters of mass-inertial asymmetry.

The technical result is achieved by the fact that in the method of balancing the rotor in one plane of correction, a rotor is installed in the supports of the balancing stand, with specified maximum permissible values of the parameters of mass-inertial asymmetry - the transverse displacement of the center of mass and the angle of deviation of the longitudinal center for relative geometry from its geometric axis, located at the ends two correction planes, one of which is a balancing one, and the other is a trial one, and having known masses, distances from the center of mass to the correction planes and, with the values of the moments of inertia, the rotor is brought into rotation, during rotation, the amplitudes and phases of the vibrations of both bearings caused by the initial rotor imbalances are first measured, then, by attaching trial weights to each of the correction planes, the amplitudes and phases of the vibrations of both bearings are again measured, after which according to the results calculated, the coefficients of the balancing sensitivity of the stand and the coefficients of mutual influence of the correction planes, determine the values and angles of the vectors of the initial imbalances in each correction plane tions, find the initial values of the parameters of mass-inertial asymmetry - the transverse displacement of the center of mass and the angle of deviation of the longitudinal GCI relative to the geometric axis of the rotor, if at least one of them exceeds a predetermined maximum permissible value, create a balancing imbalance in the balancing correction plane, after calculating it values and angular position, after which the residual values of the parameters of mass-inertial asymmetry are determined, and then the rotor balancing is judged by According to the invention, when creating a balancing imbalance, first, the appearance of an imbalance in the balancing correction plane, which excludes the initial imbalance in this correction plane, is then modeled, then taking into account the coefficient of interference of the correction planes, the appearance of the imbalance in the balancing correction plane, providing the values of the transverse displacement of the center of mass and the deviation angle eniya GTSOI relative longitudinal geometric axis of the rotor to values not greater than respective predetermined limit values.

Also according to the invention, in order to minimize errors in determining the amplitudes and phases of vibration of the supports when using technological equipment rigidly connected to the rotor, test weights are attached twice to each of the correction planes in two mutually opposite angular positions, followed by averaging of the measurement results, one of the correction planes belongs to technological equipment.

In addition, in order to minimize errors in determining the coefficients of the balancing sensitivity of the stand and the coefficients of the interaction of the correction planes when using technological equipment that is rigidly connected to the rotor, the measurements of the vibrations of the supports during the rotation of the rotor in the initial state are performed twice, while the second measurement is performed after disconnecting the technological equipment and turning the rotor 180 degrees around its axis and its repeated rigid connection with technological equipment.

Modeling balancing imbalances using the coefficients of interaction of the correction planes allows us to confirm the possibility of achieving mass inertial asymmetry parameters that do not exceed the maximum allowable values when balancing the rotor in one correction plane and more accurately determine the weight and angle of installation of the balancing weight without additional balancing operations.

When using technological equipment, attaching test weights twice to each of the correction planes in two mutually opposite angular positions, followed by averaging of the measurement results, reduces the measurement errors caused by a possible shift of the center of the correction plane relative to the axis of rotation.

Also, when using technological equipment, measurements of the vibrations of the supports during the rotation of the rotor in the initial state are performed twice, while the second measurement is performed after disconnecting the technological equipment, turning the rotor 180 degrees around its axis and re-connecting it rigidly with the technological equipment, which allows to reduce errors caused by possible bias of the geometric axis of the rotor relative to the axis of rotation of technological equipment.

The method can be implemented both on a horizontal and a vertical balancing stand.

The presence in the claimed invention features that distinguish it from the prototype, allows us to consider it appropriate to the condition of "novelty."

New features that contain a distinctive part of the claims are not identified in inventions of a similar purpose, on this basis we can conclude that the claimed invention meets the condition of "inventive step".

Figure 1 shows the rotor installed in the supports of the vertical balancing stand.

, характеризуемый значением B и углом α в связанной с ротором системе координат.Figure 2 shows a vector diagram for a balancing plane in which an imbalance

characterized by the value of B and the angle α in the coordinate system associated with the rotor.

, характеризуемый значением H и углом β в связанной с ротором системе координат.Figure 3 shows a vector diagram for a trial correction plane in which an imbalance is present.

characterized by the value of H and the angle β in the coordinate system associated with the rotor.

Figure 4 shows the design of the rotor with operating in two - balancing (B) and trial (H) - correction planes imbalances. The parameters of the mass-inertial asymmetry of the rotor are also shown, the presence of which causes the appearance of imbalances in the balancing and test planes for the correction of the unbalanced rotor rotating in the bearings.

Figure 5 shows the vector diagrams of imbalances operating in the correction planes during and after reduction of the values of the mass-inertial asymmetry of the rotor to values not exceeding the specified maximum permissible values.

The method is implemented as follows. Rotor 1 (Fig. 1) having two correction planes, one of which is balancing 2, that is, it is intended for both temporary installation of trial and permanent installation of balancing weights, and the other is trial 3, that is, it is used only for temporary installation test weights, set and rotate in supports 5 and 6 of stand 4, which has sensors 7 and 8, measuring the vibrations of supports 5 and 6, respectively, and a sensor 9 that detects the phases of the vibrations of supports 5 and 6. The amplitudes are measured at a constant rotational speed of rotor 1 (A) and phases (<p ) vibrations of supports 5 and 6 using sensors 7, 8 and 9.

If the rotor 1 does not have a trial correction plane 3, this plane can be formed by using various options of technological equipment (not shown in the drawing), rigidly connected to the rotor. In this case, the function of the test correction plane will be performed by the correction plane formed by the tooling, located at a known distance from the rotor's center of mass and having a known installation radius of test weights.

Rotor 1 also has specified maximum permissible values of the parameters of mass-inertial asymmetry and has known masses, distances from the center of mass to the correction planes 2 and 3, the installation radii of balancing weights r _in and r _n in the correction planes 2 and 3, and axial and equatorial moments inertia.

During the balancing experiment, the rotor 1 is first brought into rotation in its initial state, that is, with initial imbalances, measured, using sensors 7, 8 and 9, of the amplitudes and phases of the vibration of the supports due to the initial asymmetry of the rotor 1. After stopping the rotor 1 in one of correction planes 2 or 3, for example, in the balancing plane of correction 2 set the first test load of known mass m _in a known angular position φm _In a known radius r _In . Again, the rotor 1 is brought into rotation, the amplitudes and phases of the vibrations of the supports 5 and 6 from the sensors 7 and 8 are measured, after which the rotor 1 is stopped. The first test load is removed and a second test load of known mass m _H in a known angular position φm _H at a known radius r _{H is} attached in a second, for example, test correction plane 3. The rotor 1 is again brought into rotation, the amplitudes and phases of the vibrations of the supports are measured using sensors 7, 8 and 9.

Then, during the processing of the obtained data, the amplitudes and phases of the vibrations of the supports are determined, which are caused only by the presence of test weights installed on the corresponding correction planes, thereby eliminating the influence of the initial imbalances on the measurement results. Then calculate the coefficients of the balancing sensitivity of the stand 4 and the coefficients of mutual influence of the correction planes 2 and 3, according to the formulas:

;

;

;

;

$$K_N=\frac{A_H^{mn}}{m_H{r}_H};$$

$$K{\phi }_N={\phi }_H^{mn}-\phi m_H;$$

;

;

$$K_{\mathrm{AT}N}=\frac{A_{\mathrm{AT}}^{mn}{m}_B{r}_B}{A_{\mathrm{AT}}^{m\mathrm{at}}{m}_H{r}_H};$$

where And _In - the amplitude of the vibration of the support 5 during rotation of the rotor with an initial imbalance;

And _N is the amplitude of vibration of the support 6 during rotation of the rotor with an initial imbalance;

- амплитуда вибрации опоры 5 при наличии пробного груза в балансировочной плоскости коррекции 2;

- the amplitude of the vibration of the support 5 in the presence of a test load in the balancing plane of correction 2;

- фаза вибрации опоры 5 при наличии пробного груза в балансировочной плоскости коррекции 2;

- phase vibration of the support 5 in the presence of a test load in the balancing plane of correction 2;

- амплитуда вибрации опоры 5 при наличии пробного груза в пробной плоскости коррекции 3;

- the amplitude of the vibration of the support 5 in the presence of a test load in the trial correction plane 3;

- амплитуда вибрации опоры 6 при наличии пробного груза в балансировочной плоскости коррекции 2;

- the amplitude of the vibration of the support 6 in the presence of a test load in the balancing plane of correction 2;

- амплитуда вибрации опоры 6 при наличии пробного груза в пробной плоскости коррекции 3;

- the amplitude of the vibration of the support 6 in the presence of a test load in the trial correction plane 3;

- фаза вибрации опоры 6 при наличии пробного груза в пробной плоскости коррекции 3;

- phase vibration of the support 6 in the presence of a test load in the trial correction plane 3;

K _B is the coefficient of balancing sensitivity of stand 1 to the value of the imbalance in the balancing plane of correction 2;

Kφ _B - coefficient of balancing sensitivity of stand 1 to the unbalance angle in the balancing plane of correction 2;

K _H is the coefficient of balancing sensitivity of the stand 1 to the imbalance value in the trial correction plane 3;

Kφ _H is the coefficient of balancing sensitivity of stand 1 to the unbalance angle in the trial correction plane 3;

K _HB is the coefficient of influence of the balancing correction plane 2 on the trial correction plane 3 in the presence of imbalance in the balancing correction plane 2;

K _BH is the coefficient of influence of the trial correction plane 3 on the balancing correction plane 2 in the presence of imbalance in the trial correction plane 3.

и

, соответственно действующих в балансировочной (фиг.2) и пробной (фиг.3) плоскостях коррекции, по формулам:Then, using the obtained coefficients, as well as the values of the amplitudes and phases of the vibrations of the supports obtained during rotation of the rotor with initial imbalances, determine the values (B, H) and angular positions (α, β) of the vectors of initial imbalances

and

respectively operating in the balancing (figure 2) and trial (figure 3) correction planes, according to the formulas:

; α_Σ=φ_B-Kφ_B;

; α _Σ = φ _B -Kφ _B ;

; β_Σ=φ_H-Kφ_H;

; β _Σ = φ _H -Kφ _H ;

where φ _B and φ _H are the phases of vibration of the supports 5 and 6, respectively, during rotation of the rotor 1 with initial imbalances;

B _H = H _Σ · K _BH ; α _H = β _Σ + 180 °;

H _B = B _Σ · K _HB ; β _H = α _Σ + 180 °;

;

;

;

;

;

;

$$\beta =arctg\frac{\sin {\beta }_{\sum }-\sin {\beta }_B}{\cos {\beta }_{\sum }-\cos {\beta }_B}.$$

и вектор-угол

отклонения продольной ГЦОИ 10 от геометрической оси 11 (фиг.4) ротора 1, по формулам:From the values and angles of the initial imbalances, as well as from the known mass, distances from the center of mass to the correction planes 2 and 3, the values of the axial and equatorial moments of inertia of the rotor, find the initial values of the transverse displacement of the center of mass and the angle of deviation of the longitudinal main central axis of inertia relative to the geometric axis rotor, which are the radius vector of the initial transverse displacement of the center of mass

and angle vector

the deviation of the longitudinal GICI 10 from the geometric axis 11 (figure 4) of the rotor 1, according to the formulas:

;

;

,

,

where M is the mass of the rotor;

- вектор начального дисбаланса, действующего в балансировочной плоскости коррекции 2 радиусом r_B;

is the vector of the initial imbalance operating in the balancing plane of correction 2 with a radius r _B ;

- вектор начального дисбаланса, действующего в пробной плоскости коррекции 3 радиусом r_H;

is the vector of the initial imbalance operating in the trial correction plane 3 of radius r _H ;

x _B is the distance from the center of mass of the rotor 1 to the balancing plane of correction 2;

x _H is the distance from the center of mass of the rotor 1 to the trial correction plane 3;

I _e - the equatorial moment of inertia of the rotor 1;

I _a is the axial moment of inertia of the rotor 1.

If the value of the transverse displacement of the center of mass ρ _nach and the angle γ _{nach of the} deviation of the longitudinal GICI 10 from the geometric axis 11 of the rotor 1 do not exceed their specified maximum permissible values (respectively ρ _dop and γ _dop ), then the balancing experiment is completed and the balancing protocol is completed, in which they indicate the obtained values of mass inertial asymmetry.

путем установки в этой плоскости коррекции балансировочного груза. Массу и угол установки балансировочного груза определяют с помощью значений вектора балансировочного дисбаланса

.If the value of at least one of the indicated initial parameters of the mass-inertial asymmetry of rotor 1 exceeds the corresponding maximum permissible value, then the imbalance in the balancing plane of correction 2 is changed, creating a balancing imbalance

by installing in this plane the correction of the balancing weight. The mass and installation angle of the balancing weight is determined using the values of the vector of the balancing imbalance

.

сначала устраняют действие начального дисбаланса

в балансировочной плоскости коррекции 2 путем моделирования в этой плоскости дисбаланса

5, равного по значению, но противоположного по направлению начальному дисбалансу

, компенсирующего действие дисбаланса

в указанной плоскости коррекции. В результате геометрическая ось 11 и продольная ГЦОИ 10 ротора 1 будут приведены к режиму квазистатической неуравновешенности, когда указанные оси пересекаются не в центре масс. При этом в пробной плоскости коррекции возникнет дополнительный дисбаланс

, образовавшийся в результате влияния балансировочной плоскости коррекции 2 с действующим в этой плоскости дисбалансом

на пробную плоскость коррекции 3, значение которого находят по формуле:To determine the values of the balancing imbalance vector

first eliminate the effect of the initial imbalance

in the balancing plane of correction 2 by modeling in this plane of imbalance

5, equal in value, but opposite in direction to the initial imbalance

compensating for the effect of imbalance

in the specified correction plane. As a result, the geometric axis 11 and the longitudinal SCOI 10 of the rotor 1 will be reduced to the regime of quasistatic imbalance, when these axes intersect not at the center of mass. In this case, an additional imbalance will occur in the trial correction plane

resulting from the influence of the balancing plane of correction 2 with the imbalance acting in this plane

on the trial correction plane 3, the value of which is found by the formula:

N _DPL1 = V _COMP · K _NV ,

будет противоположным угловому положению дисбаланса

, так как он образован в результате взаимовлияния плоскостей коррекции.and the angular position of the additional imbalance

will be the opposite of the angular position of the imbalance

, since it is formed as a result of the mutual influence of the correction planes.

находят значение и угловое положение дисбаланса

в пробной плоскости коррекции 3, путем геометрического сложения векторов двух дисбалансов, действующих в этой плоскости - начального

и дополнительного

по формуле:After determining the parameters of the additional imbalance

find the value and the angular position of the imbalance

in the trial correction plane 3, by geometric addition of the vectors of two imbalances operating in this plane - the initial

and additional

according to the formula:

в балансировочной плоскости коррекции в противоположном направлении дисбалансу

, при этом в пробной плоскости коррекции возникает дисбаланс

, значение которого уравнивается со значением

, с помощью коэффициента взаимовлияния плоскостей коррекции.Then simulate the creation of an imbalance

in the balancing plane of correction in the opposite direction to the unbalance

while an imbalance occurs in the trial correction plane

whose value is equalized with the value

using the coefficient of mutual influence of the correction planes.

по формуле:To do this, first determine the value of the imbalance

according to the formula:

,

,

, на которое увеличилось значение дисбаланса

, в результате действия дисбаланса

в балансировочной плоскости коррекции, по формуле:and then determine the value

, which increased the value of imbalance

as a result of the imbalance

in the balancing correction plane, according to the formula:

Н _ДПЛ2 = В _CORR · К _НВ ,

, возникшего в результате увеличения дисбаланса

на значение

, по формуле:then determine the value of the imbalance

resulting from an increase in imbalance

on value

, according to the formula:

$${\overrightarrow{H}}_{\mathrm{TO}\mathrm{ABOUT}RR}={\overrightarrow{H}}_{\mathrm{TO}\mathrm{ABOUT}MP}+{\overrightarrow{H}}_{DPL2}.$$

и

, действующие в плоскостях коррекции 2 и 3, равны по значению, но противоположны по направлению, а указанные оси 10 и 11 пересекаются в центре масс, что указывает на отсутствие поперечного смещения центра масс с геометрической оси 11 ротора 1 и, соответственно, не превышению предельно допустимых значений данного параметра.As a result, the geometric axis 11 of the rotor 1 and its longitudinal SCSI 10 will be reduced to the momentary imbalance mode, when the imbalances

and

acting in the correction planes 2 and 3 are equal in value but opposite in direction, and the indicated axes 10 and 11 intersect in the center of mass, which indicates the absence of transverse displacement of the center of mass from the geometric axis 11 of rotor 1 and, accordingly, not exceeding the maximum valid values for this parameter.

Next, calculate the expected (in the moment of imbalance) value γ _{CORR of the} angle of deviation of the longitudinal SCOI 10 from the geometric axis 11 of the rotor 1, according to the formula:

where L is the distance between the correction planes 2 and 3.

используя соответствующие параметры смоделированных в балансировочной плоскости коррекции 2 векторов дисбалансов

и

. После чего по значению вектора балансировочного дисбаланса $${\overrightarrow{B}}_{БАЛ}$$

определяют массу балансировочного груза, установку которого производят в угловом положении, соответствующем угловому положению $${\overrightarrow{B}}_{БАЛ}.$$

Для определения массы и угла установки балансировочного груза используют формулы:In cases where the value of _CORR does not exceed its maximum permissible value of γ _extra , determine the value of _BAL and the angular position α _{BAL of the} vector of balancing imbalance $${\overrightarrow{B}}_{B\mathrm{BUT}L},$$

using the corresponding parameters of 2 imbalance vectors simulated in the balancing plane of correction

and

. Then, according to the value of the vector of balancing imbalance $${\overrightarrow{B}}_{B\mathrm{BUT}L}$$

determine the mass of the balancing load, the installation of which is carried out in an angular position corresponding to the angular position $${\overrightarrow{B}}_{B\mathrm{BUT}L}.$$

To determine the mass and installation angle of the balancing load, use the formulas:

,

,

, а α_КОРР - угловое положение дисбаланса

.where α _COMP - the angular position of the imbalance

, and α _CORR - the angular position of the imbalance

.

After that, the mass of the rotor 1 is adjusted by attaching the balancing weight to the balancing plane 2, thereby ensuring that both parameters of the mass-inertial asymmetry are brought to values not exceeding the maximum permissible ones.

поперечного смещения центра масс с оси симметрии 11 (минимально возможное для ротора 1), которое может быть достигнуто путем изменения дисбаланса в балансировочной плоскости коррекции 2 для уменьшения значения угла отклонения продольной ГЦОИ 10 до предельно допустимого значения γ_доп по формуле:In cases where the value of _CORR will exceed the maximum permissible value of γ _extra , calculate the estimated value

the lateral displacement of the center of mass from the axis of symmetry 11 (the smallest possible for rotor 1), which can be achieved by changing the imbalance in the balancing plane of correction 2 to reduce the deviation angle of the longitudinal SCSI 10 to the maximum permissible value γ _dop according to the formula:

будет превышать заданное предельно допустимое значение ρ_доп, балансировочный эксперимент прекращают, а ротор 1 бракуют и направляют изготовителю на перекомпоновку. В ином случае, то есть когда полученное значение поперечного смещения центра масс ротора 1 не превышает своего предельно допустимого значения, определяют значение вектора дисбаланса $${\overrightarrow{B}}_{КОРР|\gamma ={\gamma }_{доп}},$$

сонаправленного вектору

и обеспечивающего достижение значения

по формуле:In cases where the received value

will exceed the specified maximum permissible value ρ _add , the balancing experiment is stopped, and the rotor 1 is rejected and sent to the manufacturer for re-arrangement. Otherwise, that is, when the obtained value of the transverse displacement of the center of mass of the rotor 1 does not exceed its maximum permissible value, determine the value of the unbalance vector $${\overrightarrow{B}}_{\mathrm{TO}\mathrm{ABOUT}RR|\gamma ={\gamma }_{d\mathrm{about}P}},$$

co-directional vector

and providing value

according to the formula:

изменится на величину

(на чертеже не показан) в результате действия дисбаланса $${\overrightarrow{B}}_{КОРР|\gamma ={\gamma }_{доп}}$$

в балансировочной плоскости коррекции, значение которой определяют по формуле:in this case, due to the interaction of the correction planes, the imbalance value

will change by

(not shown) as a result of the imbalance $${\overrightarrow{B}}_{\mathrm{TO}\mathrm{ABOUT}RR|\gamma ={\gamma }_{d\mathrm{about}P}}$$

in the balancing correction plane, the value of which is determined by the formula:

.

.

и угловое положение

вектора балансировочного дисбаланса

, используя соответствующие параметры смоделированных в балансировочной плоскости коррекции 2 векторов дисбалансов $${\overrightarrow{B}}_{КОРР|\gamma ={\gamma }_{доп}}$$

и

. После чего по значению вектора балансировочного дисбаланса

определяют массу балансировочного груза, установку которого производят в угловом положении, соответствующем угловому положению

. Для определения значения балансировочного дисбаланса, массы и угла установки балансировочного груза используют формулы:Then determine the value

and angular position

balancing imbalance vectors

using the corresponding parameters of 2 imbalance vectors simulated in the balancing correction plane $${\overrightarrow{B}}_{\mathrm{TO}\mathrm{ABOUT}RR|\gamma ={\gamma }_{d\mathrm{about}P}}$$

and

. Then, according to the value of the vector of balancing imbalance

determine the mass of the balancing load, the installation of which is carried out in an angular position corresponding to the angular position

. To determine the value of the balancing imbalance, mass and installation angle of the balancing load, use the formulas:

,

,

,

,

After that, the mass of the rotor 1 is adjusted by attaching the balancing weight to the balancing plane 2, thereby ensuring that both parameters of the mass-inertial asymmetry are brought to values not exceeding the maximum permissible ones.

With this sequence of actions, two parameters of rotor mass-inertia asymmetry are brought simultaneously — the lateral displacement of the center of mass and the angle of deviation of the longitudinal center for the rotor geometrical axis — to values that do not exceed the corresponding maximum permissible values (specified in the rotor operating documentation) with a minimum displacements of the center of mass from the geometric axis and, accordingly, a reduction in the number of balancing operations and the balancing time of the rotor, as well as An increase in the information content of the rotor balancing process and the accuracy of calculating the mass and angular position of the balancing load are being enhanced.

Experimental testing conducted on a vertical balancing bench with bearings made in the form of tapered gas-static bearings confirmed the high accuracy and efficiency of the method.

Attaching test weights twice to each of the correction planes in two mutually opposite angular positions, followed by averaging of the measurement results, reduces the errors caused by the possible lateral displacement of the centers of the correction planes from the axis of rotation associated with the displacement of the centers of the circles along which the places for setting the balancing and test cargo.

Performing measurements of the vibrations of the supports, twice, during rotation of the rotor, rigidly connected to the technological equipment in the initial state and after the rotor rotates 180 degrees around its axis with its repeated rigid connection with the technological equipment, and then with subsequent averaging of the obtained values, allows to reduce errors, associated with the imperfect manufacturing of the mating surfaces of the rotor and the tool, a possible skew of the axis of symmetry of the rotor relative to the axis of rotation of the tooling.

Claims (3)

1. The method of balancing the rotor in one correction plane, namely, that a rotor is installed in the supports of the balancing stand, with specified maximum permissible values of the parameters of mass-inertial asymmetry, having two correction planes located at the ends, one of which is a balancing plane, and the other - trial, and having known mass, distances from the center of mass to the correction planes, values of the moments of inertia, the rotor is brought into rotation, during rotation, the amplitudes and phases of the vibrations of both Ohr caused by the initial rotor imbalances, then, attaching test weights to each of the correction planes, again determine the amplitudes and phases of vibration of both supports, after which the coefficients of the balancing sensitivity of the bench and the coefficients of interference of the correction planes are calculated, and the values and angles of the vectors of the initial imbalances in each correction plane, find the initial values of the parameters of the mass-inertial asymmetry of the rotor, if at least one of them exceeds of a maximum permissible value create a balancing imbalance in the balancing plane of correction, after calculating its value and the angular position, then determine the residual values of the parameters of mass inertial asymmetry, and then judge the balancing of the rotor by comparing the residual and specified maximum permissible values of the parameters of mass inertial asymmetries, characterized in that when creating a balancing imbalance, the appearance of an imbalance in the balancing square is first modeled -plane correction, ensuring the exclusion of the initial imbalance in the correction plane and with the interference correction coefficient planes simulate the appearance of imbalance correction in the balancing plane providing actuation parameter values mass-inertia rotor asymmetry to values not greater than respective predetermined limit values. 2. The method according to claim 1, characterized in that when using technological equipment rigidly connected to the rotor, test weights are attached twice to each of the correction planes in two mutually opposite angular positions, followed by averaging of the measurement results, and one of the correction planes belongs to the technological equipment . 3. The method according to claim 1 or claim 2, characterized in that when using technological equipment rigidly connected to the rotor, the measurement of the vibrations of the supports when the rotor rotates in the initial state is performed twice, while the second measurement is performed after disconnecting the technological equipment and turning the rotor 180 degrees around its axis and its repeated rigid connection with technological equipment.

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