CN117433725A - Vane vibration displacement strain relation calibration test method of integral impeller - Google Patents
Vane vibration displacement strain relation calibration test method of integral impeller Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/16—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H9/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by using radiation-sensitive means, e.g. optical means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
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Abstract
The invention discloses a vane vibration displacement strain relation calibration test method of an integral impeller, which comprises the following steps: determining the multi-order resonance frequency of a blade to be tested; a counterweight component is arranged on the non-test blade so as to lead the natural frequency of the non-test blade to be far away from the resonance frequency of the blade to be tested; and exciting the integral impeller through a vibrating table, respectively measuring vibration displacement and vibration strain of the blade to be tested under each order of resonance frequency by adopting a non-contact measurement technology, and fitting to obtain a calibration coefficient of the vibration displacement strain relation of the blade to be tested under each order of resonance frequency. The vane vibration displacement strain relation calibration test method of the integral vane wheel can cover the multi-order resonance frequency of the test required by the vane to be tested, can accurately scan the vibration displacement and strain distribution of the surface of the vane to be tested, has high detection speed and high precision, is easy to operate, and can accurately obtain the calibration coefficient of the vibration displacement strain relation of the vane to be tested.
Description
Technical Field
The invention relates to the technical field of calibration of a blade vibration strain relation of an aeroengine, in particular to a method for calibrating a blade vibration displacement strain relation of an integral impeller.
Background
Blade tip amplitude measurement and blade vibration strain monitoring of an aeroengine are necessary means for obtaining blade vibration characteristics and evaluating vibration loads of the blade, vibration strain in blade work is obtained, the method has important significance for evaluating whether the blade meets the vibration-resistant design, whether the blade can resist high-cycle fatigue damage and other parameters, and according to different monitoring modes, the blade vibration monitoring technology is mainly divided into blade tip amplitude measurement and blade vibration strain monitoring.
Blade tip amplitude measurement uses tip timing technology, only need processing several sensor mounting holes on the receiver can, detect tip vibration displacement through the sensor of installing on the receiver, and sensor easy dismounting can effectively acquire information such as resonant frequency, excitation order, vibration amplitude and phase of blade. The method has the advantages that the blade tip amplitude measurement has less refitting to the aeroengine, the early preparation period is short, the vibration conditions of all blades can be measured simultaneously, and the sensor failure caused by factors such as centrifugal load with high rotating speed can be avoided. However, the main disadvantage of the technology is that the vibration strain value of the blade cannot be directly measured, if blade high-cycle fatigue damage assessment and vibration resistance design are to be performed by using blade tip amplitude measurement data, the measured vibration displacement is converted into vibration load (vibration stress level) which can intuitively reflect the bearing of the blade, and the corresponding relation between the vibration displacement of the blade and the maximum stress point strain is required to be obtained. And because the blade has multi-order resonance frequencies, when vibrating at different resonance frequencies, the vibration stress distribution of the blade is different, and the positions of maximum stress points are different. The accuracy of the results of blade vibration strain distribution calculation, maximum vibration strain measuring point determination and vibration displacement-strain relation calibration is difficult to guarantee by using a finite element method, and test verification is lacked.
The vibration strain monitoring of the blade is to paste a strain gauge at the maximum stress point of the blade, and directly measure the strain of the blade under the high-speed rotation state of the blade through the strain gauge, and the vibration strain monitoring device has the advantages that the resonance frequency, excitation order, vibration strain and other information of the blade can be directly obtained, but because the blade is under the high-speed rotation state, a slip ring lead or a telemetering antenna is required to be configured to transmit vibration strain signals, the slip ring lead or the telemetering antenna is required to be refitted to a rotor, the additional mass of the rotor is increased, the original dynamic characteristics of the rotor are easy to change, the slip ring lead is required to be provided with an additional cooling system, the telemetering antenna is required to be provided with a special signal receiving device, the application is poor, and the steps of pasting of the strain gauge, the lead, refitting of the rotor, the slip ring lead or the telemetering antenna are long in period and complex in procedure, the cost is limited by a channel of the slip ring lead, and the vibration strain measurement cannot be performed on all blades of the whole impeller. Meanwhile, the strain gauge and the leads thereof are easy to lose efficacy under the centrifugal load and airflow flushing at high rotation speed, so that the survival rate of the strain gauge is low, and the test result is influenced.
Disclosure of Invention
The invention provides a vane vibration displacement strain relation calibration test method of an integral vane wheel, which aims to solve the technical problem that the vibration displacement and strain relation in the vane tip amplitude measurement of the integral vane wheel is difficult to accurately convert.
A vane vibration displacement strain relation calibration test method of an integral impeller comprises the following steps:
s100: determining the multi-order resonance frequency of a blade to be tested;
s200: all blades except the blade to be tested in the integral impeller are set as non-test blades, and a counterweight component is arranged on the non-test blades so that the natural frequency of the non-test blades is far away from the resonance frequency of the blade to be tested;
s300: and (3) exciting the integral impeller through the vibrating table respectively at the multi-order resonant frequencies in the step (S100), and respectively measuring the vibration displacement and the vibration strain of the blade to be tested at each order resonant frequency by adopting a non-contact measurement technology, so as to obtain the calibration coefficient of the vibration displacement strain relation of the blade to be tested at each order resonant frequency by fitting.
Preferably, step S300 specifically includes:
s301: exciting the integral impeller through a vibrating table at one of the first-order resonance frequencies in the step S100;
s302: measuring the vibration displacement of the blade to be tested by a laser displacement sensor, and measuring the maximum vibration stress area and the maximum vibration strain value of the blade to be tested by a full-field three-dimensional scanning laser vibrometer or DIC digital image correlation method;
s303: fitting to obtain a calibration coefficient of the vibration displacement strain relation of the blade to be tested under the order resonance frequency;
s304: steps S301 to S303 are repeated while changing the excitation frequency of the vibration table.
Preferably, the laser displacement sensor is erected right above the blade to be tested, and the measuring direction of the laser displacement sensor is perpendicular to the blade body surface of the blade to be tested.
Preferably, the excitation frequency of the vibration table is 0.1 Hz-20 kHz.
Preferably, after step S300, further includes:
s400: and converting the blade to be tested which is subjected to the calibration test into a non-test blade, converting one of the non-test blades which is not subjected to the calibration test into a new blade to be tested, and repeating the steps S100-S300 to perform the calibration test on the new blade to be tested.
Preferably, the counterweight assembly comprises a fixing clamp and a flexible counterweight block, wherein the flexible counterweight block is arranged between the fixing clamp and the non-test blade in a cushioning mode, and the fixing clamp is used for clamping and fixing the flexible counterweight block on the non-test blade.
Preferably, the flexible weights on different non-test blades differ in weight and/or the clamping positions of the weight assemblies on different non-test blades differ.
Further, the step S200 specifically includes:
s201: the positioning seat is used for being clamped on the non-test blade, a guide groove is formed in the positioning seat along the side edge of the non-test blade, the guide groove is used for being inserted into the counterweight assembly and used for guiding sliding of the counterweight assembly, and a scale mark is arranged on one side of the guide groove;
s202: all blades except the blade to be tested in the integral impeller are set to be non-test blades, the positioning seat is clamped on the non-test blades, the counterweight assembly is inserted into the guide groove and the position of the counterweight assembly is adjusted through the scale marks, and then the counterweight assembly is clamped and fixed on the non-test blades, so that the natural frequency of the non-test blades is far away from the resonance frequency of the blade to be tested, and the clamping positions of the counterweight assembly on different non-test blades are different.
Preferably, before step S300, the method further comprises:
install whole impeller to the shaking table through installation mechanism, installation mechanism includes base, clamping ring, locking subassembly and acceleration sensor, the base be used for with the shaking table is connected, be equipped with on the base and be used for wearing to establish whole impeller's reference column, the clamping ring cover is located on the reference column and be used for the butt whole impeller keeps away from the one end of base, locking subassembly with the clamping ring is connected and is used for driving the clamping ring will whole impeller compress tightly in on the base, acceleration sensor install in on the clamping ring and be used for monitoring the shaking table transmits vibration acceleration on the whole impeller.
Preferably, step S100 specifically includes:
s101: obtaining vibration characteristics and vibration displacement response of the blade to be tested in a rotating state through blade tip amplitude measurement;
s102: multiple order resonant frequencies of the blade to be tested are determined over a range of vibration displacements of interest.
The invention has the following beneficial effects:
according to the blade vibration displacement strain relation calibration test method of the integral impeller, the integral impeller is excited through the vibration table, namely, excitation is carried out in a non-rotating state of the blade to be tested, large excitation acceleration which can cause high cycle fatigue damage to the blade is not required to be applied, medium and small excitation acceleration which is only required to be applied within the capacity range of the vibration table is required to ensure that the multi-order resonance frequency (the highest resonance frequency is up to 10kHz to 20 kHz) of the blade to be tested can be covered, and the vibration displacement and the vibration strain of the blade to be tested are measured by adopting a non-contact measurement technology, so that the vibration displacement and the stress distribution of the surface of the blade to be tested can be accurately scanned, the inaccuracy defect of a finite element calculation method in the vibration stress distribution calculation, the maximum vibration strain measurement point determination and the vibration displacement strain relation conversion is effectively overcome, a large amount of time is not required to be spent for working the surface grinding level and pasting strain pieces, the number of strain measurement points is not limited, the additional quality influence on the blade to be tested is not generated, the requirement on the test environment and the operation personnel is low, and the method has the advantages of easy detection and high precision and high operation speed. And secondly, a counterweight component is arranged on the non-test blade before excitation, so that the natural frequency of the non-test blade is far away from the resonance frequency of the blade to be tested, the excitation energy of the vibration table is effectively prevented from being lost due to the coupling resonance of the non-test blade and the blade to be tested, adverse effects on test results are avoided, fatigue damage caused by the resonance of the non-test blade in the test process can be avoided, and the blade is effectively protected.
In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a step diagram of a method for calibrating a blade vibration displacement strain relationship of an integral impeller according to an embodiment of the present invention;
FIG. 2 is a step diagram of a method for calibrating a blade vibration displacement strain relationship of an integral impeller according to another embodiment of the present invention;
FIG. 3 is a top view of a mounting mechanism provided by an embodiment of the present invention;
FIG. 4 is a schematic cross-sectional view of the mounting mechanism shown in FIG. 3 taken along the direction A-A;
FIG. 5 is an enlarged partial view of region B of the mounting mechanism shown in FIG. 4;
fig. 6 is a schematic structural diagram of a positioning seat according to an embodiment of the present invention.
Legend description:
1. an integral impeller; 11. blades to be tested; 12. non-test leaves; 2. a counterweight assembly; 21. a fixing clamp; 22. a flexible balancing weight; 3. a laser displacement sensor; 4. a mounting mechanism; 41. a base; 411. positioning columns; 42. a compression ring; 43. a locking assembly; 44. an acceleration sensor; 5. a positioning seat; 51. a guide groove; 6. and positioning the clamping claw.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawing figures, but the invention can be practiced in a number of different ways, as defined and covered below.
Fig. 1 to 6 together show a vane vibration displacement strain relation calibration test method for an integral vane of an aero-engine, which is used for performing a vane vibration displacement strain relation calibration test on the integral vane of the aero-engine, and has the advantages of high detection efficiency, high detection precision, simple and convenient operation, and is beneficial to accurately evaluating whether the vane meets the vibration-resistant design or not and whether the vane can resist high-cycle fatigue damage or not.
As shown in FIG. 1, the vane vibration displacement strain relation calibration test method of the integral impeller comprises the following steps:
s100: determining the multi-order resonance frequency of the blade 11 to be tested;
s200: setting all blades except the blade 11 to be tested in the integral impeller 1 as non-test blades 12, and arranging the counterweight assembly 2 on the non-test blades 12 so as to enable the natural frequency of the non-test blades 12 to be far away from the resonance frequency of the blade 11 to be tested;
s300: and (3) exciting the integral impeller 1 through a vibrating table at the multi-order resonant frequency in the step (S100), respectively measuring the vibration displacement and the vibration strain of the blade 11 to be tested at each order resonant frequency by adopting a non-contact measurement technology, and fitting to obtain the calibration coefficient of the vibration displacement strain relation of the blade 11 to be tested at each order resonant frequency.
Referring to fig. 3 and 4, one of the blades of the integral impeller 1 is set as a blade 11 to be tested, and the other blades are set as non-test blades 12, it should be understood that the blade 11 to be tested is not a fixed blade, that is, the blade 11 to be tested and the non-test blade 12 can be mutually converted, the blade 11 to be tested which has completed the calibration test can be converted into the non-test blade 12, and the non-test blade 12 which has not been subjected to the calibration test can be converted into a new blade 11 to be tested, which only needs to ensure that at least one blade 11 to be tested which has not been subjected to the calibration test exists in each calibration test.
Specifically, the blade tip amplitude measurement can be adopted in advance to obtain a multi-order mode with larger vibration displacement (the blade tip amplitude measurement is concerned with), the multi-order resonance frequency of the blade 11 to be tested is determined, then a counterweight component 2 is arranged on all the non-test blades 12, the mass of each non-test blade 12 is changed through the counterweight component 2, the natural frequency of the non-test blade 12 is far away from the resonance frequency of the blade 11 to be tested, the natural frequency of the non-test blade 12 is prevented from being too close to the resonance frequency of the blade 11 to be tested to generate resonance, finally the vibration displacement and vibration strain of the whole impeller 1 are measured under the non-rotating state of the whole impeller 1 through a vibration table according to the obtained multi-order resonance frequency parameter, and the calibration coefficient of the vibration displacement strain relation of the blade 11 to be tested under each order resonance frequency is obtained through fitting according to the measurement result under the multi-order resonance frequency.
According to the blade vibration displacement strain relation calibration test method of the integral impeller, vibration is conducted on the integral impeller 1 through the vibration table, namely vibration is conducted in a non-rotating state of the blade 11 to be tested, large excitation acceleration which can enable the blade to be subjected to high cycle fatigue damage is not needed to be applied to the blade, medium and small excitation acceleration which is within the capacity range of the vibration table is not needed to be applied, the multi-order resonance frequency (the highest resonance frequency is up to 10kHz to 20 kHz) of the blade 11 to be tested is ensured to be capable of being covered, and because the blade 11 to be tested is in a non-rotating state, vibration displacement and vibration strain of the blade 11 to be tested are measured through a non-contact measurement technology, the vibration displacement and stress distribution of the surface of the blade 11 to be tested can be accurately scanned, the inaccuracy defect of a finite element calculation method in the vibration stress distribution calculation, the maximum vibration strain determination and conversion of the vibration displacement strain relation is effectively overcome, a large amount of time is not needed to be spent for carrying out surface grinding and pasting a strain gauge, the number of strain measurement points is not limited, the blade 11 to be tested is not prone to be influenced by additional quality, requirements on the blade 11 to be tested, and the requirements on environment are met, and the operation speed is low, and the operation speed is high. Secondly, the counterweight component 2 is arranged on the non-test blade 12 before excitation, so that the natural frequency of the non-test blade 12 is far away from the resonance frequency of the blade 11 to be tested, the excitation energy of the vibration table is effectively prevented from being lost due to the coupling resonance between the non-test blade 12 and the blade 11 to be tested, adverse effects on test results are avoided, fatigue damage caused by the resonance of the non-test blade 12 in the test process is avoided, and the blade is effectively protected.
Preferably, step S300 specifically includes:
s301: exciting the integral impeller 1 through a vibrating table at one of the first-order resonance frequencies in the step S100;
s302: measuring the vibration displacement of the blade 11 to be tested through a laser displacement sensor 3, and measuring the maximum vibration stress area and the maximum vibration strain value of the blade 11 to be tested through a full-field three-dimensional scanning laser vibrometer or DIC digital image correlation method;
s303: fitting to obtain a calibration coefficient of the vibration displacement strain relation of the blade 11 to be tested under the order resonance frequency;
s304: steps S301 to S303 are repeated while changing the excitation frequency of the vibration table.
Specifically, in one embodiment, a full-field three-dimensional scanning type laser vibration meter is used for measuring the maximum vibration stress area and the maximum vibration strain value of the blade 11 to be tested, the full-field three-dimensional scanning type laser vibration meter is provided with wide-band (at least 100 kHz) measurement capability, can rapidly scan the surface of the blade 11 to be tested and flexibly define the measurement area and the measurement point, can realize scanning vibration measurement in three directions X, Y, Z by controlling the deflection angle of a scanning mirror, and is provided with special three-dimensional vibration strain measurement analysis software, so that the three-dimensional array of the blade 11 to be tested and the surface stress distribution and the strain magnitude of the blade to be tested can be intuitively displayed, thereby flexibly defining a geometric unit and the scanning point.
In another embodiment, the maximum vibration stress area and the maximum vibration strain value of the blade 11 to be tested can also be measured by a DIC (Digital Image Correlation) digital image correlation method. And a digital speckle correlation method and a photogrammetry technology are adopted, a binocular stereoscopic vision technology is combined, speckle or mark point images of the deformation stage of the blade 11 to be tested are acquired in real time, a graph correlation algorithm and a photogrammetry algorithm are utilized for carrying out three-dimensional matching on the deformation points of the surface of the blade 11 to be tested, and three-dimensional space coordinates of the matching points are reconstructed. And carrying out smooth processing and visual analysis on the displacement field data and the strain information, thereby realizing rapid, high-precision, real-time and non-contact three-dimensional strain and displacement measurement. The displacement and strain distribution of the surface of the blade 11 to be tested can be accurately calculated by adopting the DIC digital image correlation method, the 3D full-field strain data distribution is clear at a glance after operation, the method of setting the strain gauge does not need to spend a great deal of time for surface grinding and pasting, meanwhile, the method can only measure the strain data on a limited point, and the method is not strict in environmental requirements like a fringe interferometry, can measure the three-dimensional deformation of the blade 11 to be tested under the dynamic load, is used for analyzing the actual deformation and strain of the blade, and has the characteristics of high speed, high precision and easiness in operation.
In summary, the vibration strain of the blade 11 to be tested is measured by adopting the non-contact strain measurement technology, compared with the traditional contact strain measurement technology, the vibration strain of the blade 11 to be tested is effectively improved in data accuracy, the data sample is increased, the test time is saved, the test data is not influenced by the weight or sharp edges of the contact devices such as the strain gauge, the adhesive tape and the like, the number of the measuring points is not limited, the strain data on discrete points can be prevented from being obtained, and the additional quality influence on the blade 11 to be tested with a light structure is avoided.
Secondly, by adjusting the excitation frequency of the vibration table and repeating the steps S301 to S303, the whole impeller 1 is excited sequentially according to the multi-order resonance frequency in the step S100, and the maximum vibration stress area and the maximum vibration strain value of the blade 11 to be tested under the multi-order resonance frequency can be accurately measured by combining a non-contact strain measurement technology, so that accurate and effective data support is provided for the calibration coefficient of the vibration displacement strain relation of the blade 11 to be tested.
As shown in fig. 3, preferably, the laser displacement sensor 3 is installed directly above the blade 11 to be tested, and the measuring direction of the laser displacement sensor 3 is perpendicular to the blade body surface of the blade 11 to be tested. The distance between the probe of the laser displacement sensor 3 and the blade body of the blade 11 to be tested is controlled within a proper range, so that the laser measuring point of the laser displacement sensor 3 is close to the blade tip of the blade 11 to be tested, and the laser measuring point of the laser displacement sensor 3 is identical to the vibration measuring position in the blade tip amplitude measurement under the complete machine rotation state, so that the laser displacement sensor 3 can accurately detect the vibration displacement of the blade 11 to be tested at the position with larger vibration amplitude, not only can provide accurate and effective data support for the calibration coefficient of the vibration displacement strain relation of the blade 11 to be tested, but also can utilize the laser displacement sensor 3 to detect the vibration condition of the blade 11 to be tested under different vibration frequencies, and further in the step S300, the blade 11 to be tested is subjected to calibration test with the vibration frequency with larger vibration displacement concerned in the blade tip amplitude measurement under the complete machine rotation state, so that the multi-order resonance frequency required to be tested of the blade 11 to be tested in the calibration test can be adjusted in place, and a set of the laser displacement sensor 3 is configured, so that the vibration test structure can be further simplified, and the vibration test steps can be realized.
Preferably, the excitation frequency of the vibration table is 0.1 Hz-20 kHz, namely the vibration table is a high-frequency vibration table, so that the vibration table can cover all resonance frequencies (the highest resonance frequency is up to 10 kHz-20 kHz) with larger vibration displacement in blade tip amplitude measurement under the whole rotation state of the blade 11 to be tested, the requirement of a calibration test of the vibration displacement and strain relation of the wideband multi-stage (up to 20 stages and above) mode blade is met, and the excitation acceleration output by the vibration table is only required to reach 10g or even 1g or less under the resonance frequency of 10 kHz-20 kHz. Therefore, compared with the conventional high-cycle fatigue test, when the vibration displacement-strain relation calibration test of the blade 11 to be tested under different resonance frequencies is carried out, the vibration table only needs to output exciting force with a certain amplitude, and the problem that the blade 11 to be tested cannot be subjected to fatigue damage due to insufficient exciting force in the high-cycle fatigue test of the blade 11 to be tested over 2000Hz and the high-cycle fatigue test cannot be carried out is avoided. The high-cycle fatigue test of the blade can only be carried out with a certain low-order (single-order) modal frequency (generally, the first-order natural frequency is not higher than 2000Hz, and the fatigue test of multiple-order modal frequency can not be carried out on a single blade) of the blade. For the high frequency high fatigue limit blade high cycle fatigue test, the excitation load required for high cycle fatigue failure to occur is even as high as 200g or more, which is far higher than the excitation load (below 100 g) provided by the vibration table at high frequency excitation, so that the high frequency (3000 Hz or more) high fatigue limit blade high cycle fatigue test cannot be implemented.
As shown in fig. 2, in another embodiment, after step S300, the method further includes:
s400: and converting the blade 11 to be tested which is subjected to the calibration test into a non-test blade 12, converting one of the non-test blades 12 which is not subjected to the calibration test into a new blade 11 to be tested, and repeating the steps S100-S300 to perform the calibration test on the new blade 11 to be tested.
Specifically, the to-be-tested blade 11 after the calibration test is completed is converted into a non-test blade 12, one of the non-test blades 12 which is not subjected to the calibration test is converted into a new to-be-tested blade 11, then the multi-order resonance frequency of the new to-be-tested blade 11 required to be tested is determined, then the counterweight components 2 are arranged on all the non-test blades 12, the natural frequencies of all the non-test blades 12 are far away from the resonance frequency of the new to-be-tested blade 11, finally the integral impeller 1 is excited through a vibrating table, the vibration displacement and the vibration strain of the new to-be-tested blade 11 are measured by adopting a non-contact measurement technology, and the calibration coefficient of the vibration displacement strain relation of the new to-be-tested blade 11 under each order resonance frequency is obtained by fitting according to the measurement result under the multi-order resonance frequency. The blades 11 to be tested are converted for a plurality of times, and calibration tests are sequentially carried out on the new blades 11 to be tested until the calibration coefficients of the vibration displacement-strain relation of all the blades (or certain specified blades) in the integral impeller 1 under different resonance frequencies are obtained.
Further, when the to-be-tested blade 11 after the calibration test is converted into the non-test blade 12, the next non-test blade 12 adjacent to the to-be-tested blade 11 is converted into a new to-be-tested blade 11, namely, the calibration test is sequentially carried out on different blades along the circumferential direction of the integral impeller 1, so that the counterweight assembly 2 is convenient to transfer, the quick test is facilitated, meanwhile, the differentiation of the blades after the calibration test and the blades without the calibration test is facilitated, and confusion is avoided.
Referring to fig. 4 and 5, the counterweight assembly 2 includes a fixing clip 21 and a flexible counterweight 22, the flexible counterweight 22 is arranged between the fixing clip 21 and the non-test blade 12 in a cushioning manner, and the fixing clip 21 is used for clamping and fixing the flexible counterweight 22 on the non-test blade 12.
Specifically, the flexible balancing weights 22 are made of rubber or silica gel materials, the two flexible balancing weights 22 are arranged, the two flexible balancing weights 22 are respectively attached to the basin surface and the back surface of the non-test blade 12, the fixing clamp 21 is provided with two elastic clamping jaws, and the two elastic clamping jaws are in one-to-one correspondence with one surfaces, away from the non-test blade 12, of the two flexible balancing weights 22, so that the two flexible balancing weights 22 are clamped and fixed on the non-test blade 12 through the two elastic clamping jaws. The flexible balancing weight 22 completely covers the elastic clamping jaw of the fixing clamp 21, so that the flexible balancing weight 22 has a large enough contact area on the non-test blade 12, and the flexible balancing weight 22 can protect the surface of the non-test blade 12 and prevent the fixing clamp 21 from scratching the non-test blade 12 while playing the roles of damping vibration reduction and clamping enhancement.
Preferably, the flexible balancing weight 22 is detachably connected with the fixing clip 21, and specifically, the flexible balancing weight 22 and the fixing clip 21 are connected into a whole through fastening connection, pin shaft connection, adhesion and the like, so that the quick clamping is convenient.
More preferably, the flexible balancing weights 22 on different non-test blades 12 have different weights and/or the clamping positions of the balancing weight assembly 2 on different non-test blades 12 are different, so that the resonance frequencies of the non-test blades 12 are staggered, the influence of larger resonance between the non-test blades 12 on the test is avoided, and the accuracy of the calibration result is further improved.
As shown in fig. 6, further, step S200 specifically includes:
s201: the positioning seat 5 is configured, the positioning seat 5 is used for being clamped on the non-test blade 12, the positioning seat 5 is provided with a guide groove 51 along the side edge of the non-test blade 12, the guide groove 51 is used for being inserted into the counterweight assembly 2 and guiding and sliding the counterweight assembly 2, and one side of the guide groove 51 is provided with a scale mark;
s202: all the blades except the blade 11 to be tested in the integral impeller 1 are set as non-test blades 12, the positioning seat 5 is clamped on the non-test blades 12, the counterweight assembly 2 is inserted into the guide groove 51 and the positions of the counterweight assembly 2 are adjusted through scale marks, and then the counterweight assembly 2 is clamped and fixed on the non-test blades 12, so that the natural frequency of the non-test blades 12 is far away from the resonance frequency of the blade 11 to be tested, and the clamping positions of the counterweight assembly 2 on different non-test blades 12 are different.
Specifically, firstly, the positioning seat 5 is fixedly clamped on the non-test blade 12, then the counterweight assembly 2 is inserted into the guide groove 51 of the positioning seat 5, the guide groove 51 is of an arc-shaped structure matched with the side edge of the non-test blade 12, the counterweight assembly 2 is slidably adjusted through the guiding action of the guide groove 51, the installation position of the counterweight assembly 2 is indicated through the scale mark, the installation position of the counterweight assembly 2 on each non-test blade 12 can be accurately adjusted, further, the clamping positions of the counterweight assemblies 2 on each non-test blade 12 are different, the assembly structure is simple and efficient, the operation is convenient, and the installation position of the counterweight assembly 2 can be positioned on the surface of the irregular non-test blade 12 without adopting complex electronic positioning equipment.
Preferably, the positioning seat 5 is hinged with a positioning claw 6, the positioning claw 6 is used for rotating to a contracted state or an expanded state relative to the positioning seat 5, the contracted state of the positioning claw 6 is attached to the positioning seat 5 and is not protruded out of one surface of the positioning seat 5 towards the non-test blade 12, the expanded state of the positioning claw 6 is used for propping against the non-test blade 12, so that the positioning seat 5 is positioned and clamped on the non-test blade 12 through the positioning claw 6, and the positioning claw 6 can enable the positioning seat 5 to be rapidly clamped or separated from the non-test blade 12 through rotating the positioning claw 6, so that the use is convenient and quick.
Further, a guiding cambered surface is arranged on one surface of the positioning claw 6, which is used for being abutted against the non-test blade 12, and the guiding cambered surface is used for guiding the positioning claw 6 to be clamped into the non-test blade 12, so that clamping stagnation and even scratch of the non-test blade 12 are avoided.
Please refer to fig. 3 and fig. 4, further comprising, prior to step S300:
the integral impeller 1 is mounted on the vibrating table through the mounting mechanism 4, the mounting mechanism 4 comprises a base 41, a pressing ring 42, a locking assembly 43 and an acceleration sensor 44, the base 41 is used for being connected with the vibrating table, a positioning column 411 used for penetrating the integral impeller 1 is arranged on the base 41, the pressing ring 42 is sleeved on the positioning column 411 and used for abutting against one end, far away from the base 41, of the integral impeller 4, the locking assembly 43 is connected with the pressing ring 42 and used for driving the pressing ring 42 to tightly press the integral impeller 1 on the base 41, and the acceleration sensor 44 is mounted on the pressing ring 42 and used for monitoring vibration acceleration transmitted to the integral impeller 1 by the vibrating table.
In this embodiment, radial positioning is performed on the integral impeller 1 through the positioning column 411, and then the integral impeller 1 is clamped and fixed through the cooperation of the compression ring 42 and the base 41, so that not only can the quick clamping of the integral impeller 1 be realized, but also the integral impeller 1 can be accurately installed on a vibration table, the vibration acceleration of the vibration table transmitted to the integral impeller 1 can be monitored in real time by using the acceleration sensor 44 on the compression ring 42, the vibration exciting force of the vibration table can be conveniently adjusted, so that the resonance frequency of the blade 11 to be tested is the same in the adaptation, and the vibration displacement and the vibration strain of the blade 11 to be tested can be accurately obtained when the vibration table outputs different vibration exciting forces (the vibration acceleration measured by the acceleration sensor 44).
Further, the positioning column 411 includes a positioning section and a connecting section that are coaxially arranged, the positioning section is matched with the shaft hole of the integral impeller 1 and is used for penetrating and fixing the integral impeller 1, the pressing ring 42 is sleeved on the connecting section, the connecting section penetrates out of one end, far away from the integral impeller 1, of the pressing ring 42 to be provided with external threads, the locking assembly 43 comprises a locking nut in threaded connection with the connecting section, and the pressing ring is tightly pressed through the threaded fit of the locking nut and the connecting section, so that the integral impeller 1 can be rapidly clamped.
Preferably, step S100 specifically includes:
s101: obtaining vibration characteristics and vibration displacement response of the blade 11 to be tested in a rotating state through blade tip amplitude measurement;
s102: the multi-order resonance frequency of the blade 11 to be tested in the vibration displacement range of interest is determined.
Specifically, vibration characteristics and vibration responses of the blades 11 to be tested in a rotating state are obtained through blade tip amplitude measurement, and blade tip timing technology is used for blade tip amplitude measurement, so that the resonance frequency, excitation order, vibration amplitude, phase and other information of the blades can be effectively obtained, modification to an engine is few, the early-stage preparation period is short, only a few laser displacement sensors are needed to be additionally arranged, sensor failure caused by centrifugal load and other factors with high rotating speed is avoided, vibration conditions of all the blades can be measured simultaneously, vibration characteristics and vibration displacement responses of all the blades in the rotating state are recorded, and further multi-order resonance frequencies of all the blades required to be tested can be rapidly determined in a concerned vibration displacement range (the defects that strain measuring points are limited, additional quality is influenced due to strain gauge and strain gauge adhesion, testing efficiency is low, period is long and the like are avoided when vibration strain is measured by using a contact strain gauge). It should be understood that the vibration displacement range of interest refers to the extent to which vibration displacement of the blade 11 to be tested may cause damage to the blade, excluding the case of a small vibration displacement.
In summary, the method for calibrating the vane vibration displacement strain relation of the integral vane provided by the embodiment of the invention has the advantages of high detection speed, high detection precision and convenient operation, and can accurately acquire the calibration coefficient of the vibration displacement strain relation of the vane 11 to be tested.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A vane vibration displacement strain relation calibration test method of an integral impeller is characterized by comprising the following steps:
s100: determining the multi-order resonance frequency of the blade (11) to be tested;
s200: all blades except the blade (11) to be tested in the integral impeller (1) are set to be non-test blades (12), and a counterweight assembly (2) is arranged on the non-test blades (12) so that the natural frequency of the non-test blades (12) is far away from the resonance frequency of the blade (11) to be tested;
s300: and (3) exciting the integral impeller (1) through the vibrating table respectively at the multi-order resonance frequency in the step (S100), respectively measuring the vibration displacement and the vibration strain of the blade (11) to be tested at each order resonance frequency by adopting a non-contact measurement technology, and fitting to obtain the calibration coefficient of the vibration displacement strain relation of the blade (11) to be tested at each order resonance frequency.
2. The method for calibrating a vane vibration displacement strain relationship of an integral impeller according to claim 1, wherein the step S300 specifically comprises:
s301: exciting the integral impeller (1) through a vibrating table at one of the first-order resonance frequencies in the step S100;
s302: measuring the vibration displacement of the blade (11) to be tested through a laser displacement sensor (3), and measuring the maximum vibration stress area and the maximum vibration strain value of the blade (11) to be tested through a full-field three-dimensional scanning laser vibration meter or a DIC digital image correlation method;
s303: fitting to obtain a calibration coefficient of the vibration displacement strain relation of the blade (11) to be tested under the resonance frequency of the order;
s304: steps S301 to S303 are repeated while changing the excitation frequency of the vibration table.
3. The method for calibrating the blade vibration displacement strain relation of the integral impeller according to claim 2, wherein the laser displacement sensor (3) is erected right above the blade (11) to be tested, and the measuring direction of the laser displacement sensor (3) is perpendicular to the blade body surface of the blade (11) to be tested.
4. The method for calibrating the blade vibration displacement strain relation of the integral impeller according to claim 1, wherein the excitation frequency of the vibrating table is 0.1 Hz-20 kHz.
5. The method for calibrating a vane vibration displacement strain relationship of an integral impeller according to claim 1, further comprising, after step S300:
s400: and converting the blade (11) to be tested which is subjected to the calibration test into a non-test blade (12), converting one of the non-test blades (12) which is not subjected to the calibration test into a new blade (11) to be tested, and repeating the steps S100-S300 to perform the calibration test on the new blade (11) to be tested.
6. The method for calibrating the blade vibration displacement strain relation of the integral impeller according to claim 1, wherein the counterweight assembly (2) comprises a fixing clamp (21) and a flexible counterweight (22), the flexible counterweight (22) is arranged between the fixing clamp (21) and the non-test blade (12) in a cushioning mode, and the fixing clamp (21) is used for clamping and fixing the flexible counterweight (22) on the non-test blade (12).
7. The method for calibrating the blade vibration displacement strain relation of the integral impeller according to claim 6, wherein the flexible balancing weights (22) on different non-test blades (12) have different weights and/or the clamping positions of the balancing weight assembly (2) on the different non-test blades (12) are different.
8. The method for calibrating a vane vibration displacement strain relationship of an integral impeller according to claim 7, wherein step S200 specifically comprises:
s201: the method comprises the steps of configuring a positioning seat (5), wherein the positioning seat (5) is used for being clamped on a non-test blade (12), a guide groove (51) is formed in the positioning seat (5) along the side edge of the non-test blade (12), the guide groove (51) is used for being inserted into the counterweight assembly (2) and guiding and sliding the counterweight assembly (2), and a scale mark is arranged on one side of the guide groove (51) of the positioning seat (5);
s202: all blades except the blade (11) to be tested in the integral impeller (1) are set to be non-test blades (12), the positioning seat (5) is clamped on the non-test blades (12), the counterweight component (2) is inserted into the guide groove (51) and the positions of the counterweight component (2) are adjusted through scale marks, and then the counterweight component (2) is clamped and fixed on the non-test blades (12), so that the natural frequency of the non-test blades (12) is far away from the resonance frequency of the blade (11) to be tested, and the clamping positions of the counterweight component (2) on different non-test blades (12) are different.
9. The method for calibrating a vane vibration displacement strain relationship of an integral impeller according to claim 1, further comprising, before step S300:
install monolithic impeller (1) to the shaking table through installation mechanism (4), installation mechanism (4) include base (41), clamping ring (42), locking subassembly (43) and acceleration sensor (44), base (41) be used for with shaking table connection, be equipped with on base (41) be used for wearing to establish monolithic impeller (1) reference column (411), clamping ring (42) cover is located on reference column (411) and be used for the butt monolithic impeller (1) keep away from the one end of base (41), locking subassembly (43) with clamping ring (42) are connected and are used for driving clamping ring (42) with monolithic impeller (1) compress tightly in on base (41), acceleration sensor (44) install in clamping ring (42) are used for monitoring shaking table transmission to vibratory acceleration on monolithic impeller (1).
10. The method for calibrating a vane vibration displacement strain relationship of an integral impeller according to claim 1, wherein step S100 specifically comprises:
s101: obtaining vibration characteristics and vibration displacement response of the blade (11) to be tested in a rotating state through blade tip amplitude measurement;
s102: a multi-order resonance frequency of the blade (11) to be tested in a vibration displacement range of interest is determined.
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| CN202311245008.XA CN117433725A (en) | 2023-09-25 | 2023-09-25 | Vane vibration displacement strain relation calibration test method of integral impeller |
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| CN202311245008.XA CN117433725A (en) | 2023-09-25 | 2023-09-25 | Vane vibration displacement strain relation calibration test method of integral impeller |
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