Same-side input double-shaft compressor tester rotor concentricity reserving method

Abstract

The invention provides a same-side input double-shaft compressor tester rotor concentricity reserving method, which belongs to aero-engine tests and comprises the following steps: determining thermal expansion displacement of an exhaust passage and a gear box support structure in a same-side input double-shaft compressor tester, according to the thermal expansion displacement and the axial distance, the thermal expansion displacement of the input flange of the biaxial compressor test piece and the thermal expansion displacement of the output flange of the gearbox are obtained through calculation, and then the estimated cold and hot state concentricity variation is obtained; according to the estimated cold and hot state concentricity variable quantity, the estimated cold state concentricity is calculated by taking the hot state concentricity as zero, and the rotor of the double-shaft compressor tester is arranged according to the estimated cold state concentricity; vibration measuring points and bearing temperature measuring points are arranged for testing, the operation state of the double-shaft compressor tester is judged through the vibration measuring points and the bearing temperature measuring points, and if the operation state meets the requirement, the estimated cold-state concentricity meets the requirement; and if the operation state does not meet the requirement, the estimated cold state concentricity is corrected.

Description

Technical Field

[0001] The present application belongs to the field of aero-engine testing, and in particular relates to a rotor concentricity reservation method for a dual-axis compressor tester with same-side input. Background Art

[0002] The dual-axis compressor tester with the same-side input usually uses two motors as the power input. After the gearbox speed increase, the two parallel drive shafts are converted into a coaxial transmission form of an outer sleeve and an inner shaft to drive the high and low pressure rotors of the dual-axis compressor test piece (usually composed of a low-pressure compressor and a high-pressure compressor). Since the dual-axis compressor test piece and the gearbox are both coaxial transmission structures, the shaft system has the characteristics of many branches and long spans, and the rotor dynamic characteristics are complex, so it is very sensitive to the concentricity of the shaft system.

[0003] like Figure 1 The figure shows a typical schematic diagram of the shaft system and support structure of a same-side input biaxial compressor tester. The biaxial compressor test piece 1 is cantilever supported and fixed to the tester exhaust duct 2 through the exhaust mounting edge. The exhaust duct 2 is fixed to the base platform through the exhaust duct front support 4 and the exhaust duct rear support 5. The exhaust duct 2 is centrally supported, and its own thermal expansion will not cause changes in the axis position, but the thermal expansion of the exhaust duct front support 4 and the exhaust duct rear support 5 will cause changes in the test piece's axis posture. The gearbox 3 is fixed to the base platform through the base 6 and is bottom supported. The thermal expansion of the base 6 and the gearbox 3 will cause the axis to float upward. The biaxial compressor test piece 1 and the gearbox 3 are high-speed and high-torque transmissions. During the installation and adjustment process, it is necessary to ensure that the concentricity between the input flange 7 of the biaxial compressor test piece 1 and the output flange 8 of the gearbox 3 is good to avoid unnecessary vibration.

[0004] When the dual-axis compressor tester is running, the exhaust temperature and pressure are both high. The supporting structures of the exhaust duct 2 and the gearbox 3 are located in a high-temperature environment. The thermal expansion and deformation of the supporting structure will cause the axis to deviate from the initial position. Therefore, it is necessary to reserve the cold concentricity to ensure that the hot shaft system is well aligned. However, due to the uneven thermal expansion of each supporting structure, it is difficult to estimate the change in cold and hot concentricity. The existing concentricity reservation method only calculates the thermal expansion and deformation of the exhaust duct and gearbox separately before the test, and performs an initial reservation evaluation. However, due to the uneven thermal expansion, the concentricity reserved by this method is poor, and it is difficult to ensure the alignment of the hot shaft system. Summary of the invention

[0005] The purpose of the present application is to provide a rotor concentricity reservation method for a dual-axis compressor tester with same-side input, so as to solve or alleviate at least one problem in the background technology.

[0006] The technical solution of the present application is: a method for reserving rotor concentricity of a dual-axis compressor tester with same-side input, comprising: S10, determining the thermal expansion displacement of the exhaust duct and the gearbox support structure in the height direction of the biaxial compressor tester with the same side input, and calculating the thermal expansion displacement of the input flange of the biaxial compressor test piece and the output flange of the gearbox in the height direction according to the thermal expansion displacement of the exhaust duct and the gearbox support structure in the height direction and the axial distance, and then obtaining the estimated cold and hot concentricity change; S20, calculating an estimated cold concentricity based on the estimated change in cold and hot concentricity, with the hot concentricity being zero, and setting a rotor of the biaxial compressor tester based on the estimated cold concentricity; S30, arranging vibration measuring points, bearing temperature measuring points and supporting structure wall temperature measuring points in the biaxial compressor tester, operating the biaxial compressor tester to perform a test, and judging the operating state of the biaxial compressor tester by the vibration measuring points and the bearing temperature measuring points; if the operating state meets the requirements, the estimated cold concentricity meets the requirements; if the operating state does not meet the requirements, correcting the estimated cold concentricity by using the data of the supporting structure wall temperature measuring points.

[0007] Preferably, the exhaust duct and gear box support structure includes an exhaust duct front support, an exhaust duct rear support, a gear box support front foot, and a gear box support rear foot.

[0008] Preferably, in step S10, the process of obtaining the estimated cold and hot concentricity variation includes: S11, acquiring temperature field data of the exhaust duct and the gearbox support structure, wherein the temperature field data includes a temperature variation; S12, obtaining structural dimension data including material, height and axial distance of the exhaust duct and the gearbox support structure, and obtaining thermal expansion data under the corresponding temperature field data of the material; S13, based on the temperature field data, the structural dimension data and the thermal expansion data, respectively calculating the thermal expansion displacement of the exhaust duct front support and the exhaust duct rear support in the height direction. , And the thermal expansion displacement of the front and rear gearbox support feet in the height direction , ; S14, according to the calculation results of the thermal expansion displacement of the exhaust duct and the gearbox support structure and the axial distance, the thermal expansion displacement of the input flange of the biaxial compressor test piece and the output flange of the gearbox in the height direction is calculated. The difference between the thermal expansion displacement of the input flange of the biaxial compressor test piece and the output flange of the gearbox is the concentricity change during the thermal expansion process, so that the estimated cold and hot concentricity change is obtained as follows: , , They are the thermal expansion displacements of the input flange of the dual-shaft compressor test piece and the output flange of the gearbox.

[0009] Preferably, the temperature field data of the temperature variation of the exhaust duct and the gearbox support structure are obtained through CFD simulation calculation, theoretical estimation and analogy analysis methods.

[0010] Preferably, the thermal expansion displacement of the exhaust duct front support and the exhaust duct rear support in the height direction is , And the thermal expansion displacement of the front and rear gearbox support feet in the height direction , The calculation method is: ; Where α is the thermal expansion coefficient of the material of the exhaust duct or gearbox support structure; ΔT is the temperature change of the exhaust duct or gearbox support structure; H Height of the exhaust duct or gearbox support structure.

[0011] Preferably, the thermal expansion displacement of the input flange of the biaxial compressor test piece and the output flange of the gearbox in the height direction is calculated by linear interpolation method, that is: ; ; Where L is the axial distance.

[0012] Preferably, the process of correcting the estimated cold concentricity using the data of the temperature measurement points on the support structure wall includes: S31, obtain the concentricity of the rotor of the biaxial compressor tester after the test and the temperature of the exhaust duct and gearbox support structure after the test , according to the exhaust duct and gearbox support structure temperature during the test , estimated cold concentricity C and concentricity after test Estimating hot concentricity during testing , and then get the estimated actual concentricity change ; S32, re-evaluate and calculate the change of hot and cold concentricity based on the actual temperature of each support structure during the test, and obtain the change of hot and cold concentricity in the test , The temperature change of the exhaust duct or gearbox support structure during the test; S33, estimated actual concentricity change The change of concentricity in hot and cold states during the test Get the corrected cold and hot concentricity change ; S34, according to the corrected cold and hot concentricity variation, the corrected cold concentricity is calculated with the hot concentricity being zero.

[0013] In order to solve the problem of significant concentricity changes caused by factors such as short axial span and high exhaust temperature of the exhaust duct support structure of the dual-axis compressor tester, this application comprehensively considers multiple influencing factors such as thermal expansion deformation of the exhaust duct support, thermal expansion deformation of the gearbox housing, thermal expansion deformation of the gearbox base, and uneven thermal expansion at different circumferential positions, thereby improving the calculation accuracy of the cold and hot concentricity changes. At the same time, this application proposes to correct the cold and hot concentricity changes based on test data, so as to effectively reserve the rotor concentricity of the dual-axis compressor tester and effectively avoid abnormal phenomena such as shaft system vibration caused by poor hot concentricity. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0015] Figure 1 Schematic diagram of the shafting support structure of a typical same-side input biaxial compressor tester.

[0016] Figure 2 A schematic diagram of a rotor concentricity reservation method for a dual-axis compressor tester with same-side input according to the present application.

[0017] Figure 3 Schematic diagram of the calculation points of thermal expansion displacement of the biaxial compressor tester with same-side input in this application. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0019] For the dual-axis compressor tester, the ambient temperature of the exhaust duct and the supporting structure of the gearbox is relatively high, and the front / rear support of the exhaust duct, the gearbox housing and the base will all produce significant thermal expansion deformation. In addition, the structural form of the same-side input causes the axial span of the front and rear supports of the exhaust duct to be shorter (about 1 / 2 of the traditional single-axis structure), and the change in hot concentricity caused by the uneven thermal expansion phenomenon is more significant. Therefore, in order to solve the problem that the rotor concentricity reserve of the dual-axis compressor tester with the same-side input is difficult to evaluate and calculate, this application proposes to comprehensively consider the thermal expansion deformation of the exhaust duct support, the gearbox housing, and the gearbox base to improve the calculation accuracy and avoid the problem of large deviation caused by single factor calculation. At the same time, the concentricity reserve is corrected based on the test data to further optimize the hot concentricity and ensure the hot alignment of the shaft system.

[0020] Concentricity reservation means that when adjusting the cold concentricity before the test, it is not adjusted according to the principle of complete alignment, but a certain deviation is reserved to compensate for the change of rotor concentricity under the influence of thermal expansion and deformation during the test, so as to ensure that the rotor is well aligned in the hot state. The most core link in this process is the estimation of the change in cold and hot concentricity. When designing a biaxial compressor tester, it is usually symmetrical relative to the axis in the horizontal direction. Therefore, the influence of thermal expansion and deformation in the horizontal direction on concentricity is relatively small. This application is mainly for the concentricity reservation in the vertical direction.

[0021] like Figure 2 As shown, the rotor concentricity reservation method of the dual-axis compressor tester with same-side input provided in the present application includes the following process: S10, determining the thermal expansion displacement of the exhaust duct and the gearbox support structure in the height direction, and calculating the thermal expansion displacement of the input flange of the biaxial compressor test piece and the output flange of the gearbox in the height direction according to the thermal expansion displacement of the exhaust duct and the gearbox support structure in the height direction and the axial distance, and then obtaining the estimated cold and hot concentricity change.

[0022] In the present application, the exhaust duct and gearbox support structure includes an exhaust duct front support, an exhaust duct rear support, a gearbox support front foot, and a gearbox support rear foot.

[0023] like Figure 3 As shown, due to the baking of high-temperature exhaust during the test, the thermal expansion displacement of the exhaust duct rear support (point C) is usually larger than the thermal expansion displacement of the exhaust duct front support (point A), and the thermal expansion displacement of the gearbox support front foot (point E) is larger than the thermal expansion displacement of the gearbox support rear foot (point F). Therefore, the thermal expansion displacement of each point is calculated separately in this application, specifically including: S11, obtaining temperature field data of the exhaust duct and the gearbox support structure through CFD simulation calculation, theoretical estimation, analogy analysis and other methods, wherein the temperature field data includes temperature variation.

[0024] S12, obtaining structural dimension data such as material, height and axial distance of the exhaust duct and the gearbox support structure according to the design drawings, and checking thermal expansion data such as thermal expansion coefficient of relevant materials under corresponding temperature field data.

[0025] S13, assuming that the biaxial compressor test piece and the exhaust duct are linearly deformed during thermal expansion, the thermal expansion displacement of the exhaust duct front support (point A) and the exhaust duct rear support (point C) in the height direction are calculated based on the temperature field data, structural dimension data and thermal expansion data. , And the thermal expansion displacement of the front and rear gearbox support feet in the height direction , , where the thermal expansion displacement of the exhaust duct and the gearbox support structure are calculated using the following formula: ; Where α is the thermal expansion coefficient of the material of the exhaust duct or gearbox support structure; ΔT is the temperature change of the exhaust duct or gearbox support structure; H Height of the exhaust duct or gearbox support structure.

[0026] Considering the large temperature difference between the gearbox base and the box body, a segmented calculation method is adopted; if the gradient of the temperature field of the exhaust duct support is large, a segmented calculation method should also be used to improve the calculation accuracy.

[0027] S14, according to the calculation results of the thermal expansion displacement of the exhaust duct and the gearbox support structure and the axial distance, the thermal expansion displacement of the input flange (point B) of the biaxial compressor test piece and the output flange (point D) of the gearbox in the height direction is calculated by linear interpolation method, that is: ; ; Where L is the axial distance.

[0028] The difference in thermal expansion displacement between the input flange (point B) of the biaxial compressor test piece and the output flange (point D) of the gearbox represents the change in concentricity during thermal expansion, so the estimated change in cold and hot concentricity is: It can be seen that when the parameters such as material thermal expansion coefficient α, support structure height H and axial distance L are determined, the change in concentricity is only related to the temperature change of the support structure, that is, .

[0029] S20, based on the estimated change in hot and cold concentricity , according to the thermal concentricity Estimated cold concentricity for standard calculations .

[0030] The rotor concentricity of the dual-axis compressor tester is adjusted with the estimated cold concentricity. When adjusting the cold concentricity, the height of the gearbox is usually adjusted with the dual-axis compressor test piece as the reference, and then the height of the power motor (not shown) inputting the gearbox on the same side is adjusted with the gearbox as the reference. It should be noted that when adjusting the concentricity in the vertical direction, the horizontal alignment should be considered at the same time.

[0031] S30, during the test, vibration measurement points were arranged at key locations of the biaxial compressor test piece, gearbox and other equipment, and bearing temperature measurement points were arranged at each support point in the biaxial compressor tester to monitor operating parameters such as vibration and bearing temperature at high speed. In addition, in order to optimize the concentricity of the exhaust duct and the gearbox support structures, wall temperature measurement points were arranged at each support position to obtain the temperature of each support structure during the test. .

[0032] If the operating performance is good, it indicates that the current hot concentricity will not produce additional vibration and the concentricity reservation plan is reasonable. If the operating performance is not good, an in-depth analysis of the measuring point data in the test is conducted to determine whether it is related to the hot alignment situation. If so, the concentricity reservation plan is optimized.

[0033] Among them, the concentricity reserve is corrected based on the measurement point data in the test to obtain the corrected reserved cold concentricity, which specifically includes: S31, due to the residual temperature of the supporting structures after the test, the concentricity will not immediately return to the initial state. The concentricity of the rotor of the biaxial compressor tester after the test can be obtained by timely inspection. , while recording the exhaust duct and gearbox support structure temperature after the test And other operating data.

[0034] Combined with the temperature of each support structure during the test , the cold concentricity C estimated before the test, the hot concentricity during the test Make an estimate to obtain the estimated hot concentricity of the test process ; The actual concentricity change can be estimated: ; S32, referring to step S14, re-evaluate and calculate the cold and hot concentricity change amount based on the actual temperature (or temperature change amount) of each supporting structure during the test to obtain the cold and hot concentricity change amount in the test , where It is the temperature change of the exhaust duct or gearbox supporting structure during the test.

[0035] S33, comprehensive comparison and estimation of actual concentricity change The change of concentricity in hot and cold states during the test The two calculation methods correct each other to reduce the influence of test data errors, structural nonlinear deformation and other factors, and obtain the corrected cold and hot concentricity change .

[0036] S34, finally repeat step S20, according to the hot concentricity As the standard, the cold concentricity is corrected and iterative verification is performed to obtain the corrected cold concentricity .

[0037] In order to solve the problem of significant concentricity changes caused by factors such as the short axial span of the exhaust duct support structure and the high exhaust temperature of the dual-axis compressor tester, the present application comprehensively considers multiple influencing factors such as the thermal expansion deformation of the exhaust duct support, the thermal expansion deformation of the gearbox body, the thermal expansion deformation of the gearbox base, and the uneven thermal expansion at different circumferential positions, thereby improving the calculation accuracy of the cold and hot state concentricity changes; at the same time, it proposes to correct the cold and hot state concentricity changes based on the test data, so as to effectively reserve the rotor concentricity of the dual-axis compressor tester and effectively avoid abnormal phenomena such as shaft system vibration caused by poor hot concentricity.

[0038] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for reserving rotor concentricity of a biaxial compressor tester with same-side input, characterized in that: include: S10, determining the thermal expansion displacement of the exhaust duct and the gearbox support structure in the height direction of the biaxial compressor tester with the same side input, and calculating the thermal expansion displacement of the input flange of the biaxial compressor test piece and the output flange of the gearbox in the height direction according to the thermal expansion displacement of the exhaust duct and the gearbox support structure in the height direction and the axial distance, and then obtaining the estimated cold and hot concentricity change; S20, calculating an estimated cold concentricity based on the estimated change in cold and hot concentricity, with the hot concentricity being zero, and setting a rotor of the biaxial compressor tester based on the estimated cold concentricity; S30, arranging vibration measuring points, bearing temperature measuring points and supporting structure wall temperature measuring points in the biaxial compressor tester, operating the biaxial compressor tester to perform a test, and judging the operating state of the biaxial compressor tester by the vibration measuring points and the bearing temperature measuring points; if the operating state meets the requirements, the estimated cold concentricity meets the requirements; if the operating state does not meet the requirements, correcting the estimated cold concentricity by using the data of the supporting structure wall temperature measuring points.

2. The rotor concentricity reservation method for a biaxial compressor tester with same-side input as claimed in claim 1, characterized in that: The exhaust duct and gear box support structure includes an exhaust duct front support, an exhaust duct rear support, a gear box support front foot, and a gear box support rear foot.

3. The rotor concentricity reservation method for a biaxial compressor tester with same-side input as claimed in claim 2, characterized in that: In step S10, the process of obtaining the estimated cold and hot concentricity variation includes: S11, acquiring temperature field data of the exhaust duct and the gearbox support structure, wherein the temperature field data includes a temperature variation; S12, obtaining structural dimension data including material, height and axial distance of the exhaust duct and the gearbox support structure, and obtaining thermal expansion data under the corresponding temperature field data of the material; S13, based on the temperature field data, the structural dimension data and the thermal expansion data, respectively calculating the thermal expansion displacement of the exhaust duct front support and the exhaust duct rear support in the height direction. , And the thermal expansion displacement of the front and rear gearbox support feet in the height direction , ; S14, according to the calculation results of the thermal expansion displacement of the exhaust duct and the gearbox support structure and the axial distance, the thermal expansion displacement of the input flange of the biaxial compressor test piece and the output flange of the gearbox in the height direction is calculated. The difference between the thermal expansion displacement of the input flange of the biaxial compressor test piece and the output flange of the gearbox is the concentricity change during the thermal expansion process, so that the estimated cold and hot concentricity change is obtained as follows: , where , They are the thermal expansion displacements of the input flange of the dual-shaft compressor test piece and the output flange of the gearbox.

4. The rotor concentricity reservation method for a biaxial compressor tester with same-side input as claimed in claim 3, characterized in that: The temperature field data of the exhaust duct and gearbox support structure temperature change are obtained through CFD simulation calculation, theoretical estimation and analogy analysis methods.

5. The rotor concentricity reservation method for a biaxial compressor tester with same-side input as claimed in claim 3, characterized in that: The thermal expansion displacement of the exhaust duct front support and the exhaust duct rear support in the height direction , And the thermal expansion displacement of the front and rear gearbox support feet in the height direction , The calculation method is: ； Where α is the thermal expansion coefficient of the material of the exhaust duct or gearbox support structure; ΔT is the temperature change of the exhaust duct or gearbox support structure; H Height of the exhaust duct or gearbox support structure.

6. The rotor concentricity reservation method for a biaxial compressor tester with same-side input as claimed in claim 5, characterized in that: The thermal expansion displacement of the input flange of the biaxial compressor test piece and the output flange of the gearbox in the height direction is calculated by linear interpolation method, that is: ； ； Where L is the axial distance.

7. The rotor concentricity reservation method for a biaxial compressor tester with same-side input as claimed in claim 6, characterized in that: The process of correcting the estimated cold concentricity using the data from the temperature measurement points on the support structure wall includes: S31, obtain the concentricity of the rotor of the biaxial compressor tester after the test and the temperature of the exhaust duct and gearbox support structure after the test , according to the exhaust duct and gearbox support structure temperature during the test , estimated cold concentricity C and concentricity after test Estimating hot concentricity during testing , and then get the estimated actual concentricity change ; S32, re-evaluate and calculate the change of hot and cold concentricity based on the actual temperature of each support structure during the test, and obtain the change of hot and cold concentricity in the test , The temperature change of the exhaust duct or gearbox support structure during the test; S33, estimated actual concentricity change The change of concentricity in hot and cold states during the test Get the corrected cold and hot concentricity change ; S34, according to the corrected cold and hot concentricity variation, the corrected cold concentricity is calculated with the hot concentricity being zero.

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