A data correction method for obtaining the labyrinth honeycomb clearance by applying high-energy X-rays

Abstract

This application belongs to the field of aero-engine design, and it is a data correction method for obtaining the clearance between labyrinth honeycombs by using high-energy X-rays. The same labyrinth honeycomb structure is measured by high-energy X-rays and putty respectively to obtain the labyrinth honeycomb data of two different measurement methods, forming two honeycomb morphologies. Then, taking the measurement result of high-energy X-rays as the main, and combining the measurement result of putty to correct the measurement result of high-energy X-rays, a correction coefficient is obtained, and the correction coefficient is used to complete the correction and calibration of the measurement result of high-energy X-rays; using the corrected data, the change law of the clearance between the labyrinth honeycombs during the test run and after the shutdown of a certain type of engine is obtained, the design of the labyrinth honeycomb structure is optimized, the problem of rotor jamming caused by too small clearance between the labyrinth honeycombs after the engine shutdown is solved, and the outfield execution rate of a certain type of engine is greatly improved.

Description

Technical Field

[0001] This application belongs to the field of aero-engine design, and particularly relates to a data correction method for obtaining the clearance between labyrinth and honeycomb by applying high-energy X-rays. Background Art

[0002] Mastering the variation law of the seal clearance between the stator and the rotor during the actual operation of an aero-engine can improve the design result of the seal structure, which is very important for improving the safety and performance retention ability of the engine. Due to the limitations of the component structure form, space and the internal environment during engine operation, the clearance of the labyrinth and honeycomb part of the engine cannot be obtained by a probe-type sensor.

[0003] As one of the advanced non-destructive testing technologies, high-energy X-ray digital imaging technology has been applied to the development of foreign aero-engines. This technology breaks through the traditional ideas and can observe and measure the working conditions of internal components at any part and any state of the engine without destroying the internal flow field of the engine, without installing measurement probes, and without being restricted by the working temperature and measurement accessibility of engine components. It can master the real-time working clearance of internal components of the engine, provide data support for clearance design and improvement, and further improve the safety and economy of the engine.

[0004] At present, the steady-state measurement accuracy of the high-energy X-ray measurement device adopted in China is 0.2 mm, which is in the same order of magnitude as the clearance between the labyrinth and honeycomb (generally in the range of 0.1 mm to 0.4 mm), and cannot meet the requirement for analyzing the variation law of the clearance between the labyrinth and honeycomb. Therefore, it is necessary to correct and calibrate the measurement data. Thus, this paper proposes a data correction method for measuring the clearance between the labyrinth and honeycomb by applying high-energy X-rays to improve the data accuracy and effectiveness and meet the requirements of actual engineering applications. Summary of the Invention

[0005] The purpose of this application is to provide a data correction method for obtaining the clearance between the labyrinth and honeycomb by applying high-energy X-rays, so as to solve the problem that the X-ray measurement device in the prior art cannot meet the requirement for analyzing the variation law of the clearance between the labyrinth and honeycomb.

[0006] The technical solution of this application is: a data correction method for obtaining the clearance of labyrinth honeycomb by applying high-energy X-rays, including: measuring the clearance of labyrinth honeycomb by high-energy X-rays, obtaining the clearance data of multiple labyrinth sealing structures based on the measurement results of high-energy X-rays, and obtaining the movement trajectory of the labyrinth relative to the honeycomb and the measured clearance results; measuring the morphology of honeycomb wear marks by using closing compound, and obtaining the morphology and size data of multiple honeycomb wear marks after the engine is disassembled based on the measurement results of closing compound; applying two measurement methods of high-energy X-rays and closing compound respectively on the same structure to obtain the clearance results of the labyrinth honeycomb at each location and the dimensional differences of the honeycomb wear marks in the radial and axial directions. Applying the measurement results of the closing compound wear marks of the corresponding structure, calibrating the clearance results of the labyrinth honeycomb at each location measured by high-energy X-rays respectively, correcting the measurement results, and determining the correction formula; calibrating the effectiveness of the correction formula through the analysis of the jamming problem after the engine stops and the test run verification.

[0007] Preferably, the method for correcting the measurement results includes: setting the radial and axial relative position values between the labyrinth and the honeycomb as A and B respectively; the radial and axial relative position values of the labyrinth and the honeycomb after engine assembly as H0 and L0 respectively; the radial and axial relative position change values of the labyrinth and the honeycomb during engine operation as H and L respectively; the radial and axial relative position change values of the labyrinth and the honeycomb measured by high-energy X-rays as H' and L' respectively; the radial and axial values of the honeycomb wear marks measured by high-energy X-rays as ΔH and ΔL respectively; the radial and axial values of the honeycomb wear marks measured by closing compound as Δh and Δl respectively; determining the true values of the relative position changes of the labyrinth honeycomb according to the values measured by the closing compound and high-energy X-rays; taking the data measured by the closing compound as the true result and correcting the measurement results of high-energy X-rays; establishing the relationship between the high-energy X-ray measurement results H' / L' and H / L to obtain two different honeycomb morphologies of high-energy X-ray measurement and closing compound measurement; taking the axial midlines of the two morphologies as the reference points, equally dividing the axis into 10 points, and correcting the two measurement results of each sealing structure; using the radial and axial values of the honeycomb wear marks measured by high-energy X-rays and closing compound to establish the relationship between the high-energy X-ray measurement results and the actual honeycomb wear mark measurement results;

[0008] Fitting the correction results of the honeycomb labyrinth to obtain the correction formula.

[0009] Preferably, the expression for the true value of the relative position change of the labyrinth honeycomb is:

[0010] H = Δh + H0

[0011] L = Δl

[0012] Preferably, the correction expression for the high-energy X-ray measurement results is:

[0013] ΔH' = f(Δh)

[0014] ΔL' = g(Δl)

[0015] Wherein, ΔH' and ΔL' are the radial and axial correction values of the honeycomb wear marks measured by high-energy X-rays.

[0016] Preferably, the expression of the high-energy X-ray measurement result H' / L' is:

[0017] H' = H0 + f(Δh)

[0018] L' = g(Δl)

[0019] Preferably, the relationship between the high-energy X-ray measurement result and the honeycomb wear mark is:

[0020] H k ' = H0 + aΔh k + b

[0021] L k ' = cΔl k + d

[0022] Where k = 1, 2, ……, 10 are the axial equally divided points, and a, b, c, and d are the

[0023] correction coefficients to be obtained. Preferably, the correction formula is:

[0024] H = 2H' - H0 - 0.05

[0025] L = 2L' - 0.016

[0026] A data correction method for obtaining the labyrinth honeycomb clearance by applying high-energy X-rays in this application. By using high-energy X-rays and putty to measure the same labyrinth honeycomb structure respectively, the labyrinth honeycomb data of two different measurement methods are obtained, forming two honeycomb morphologies. Then, mainly based on the high-energy X-ray measurement result, combined with the putty measurement result, the high-energy X-ray measurement result is corrected to obtain the correction coefficient, and the correction coefficient is used to complete the correction and calibration of the high-energy X-ray measurement result; using the corrected data, the change law of the labyrinth honeycomb clearance during the test run and after the stop of a certain type of engine is obtained, the labyrinth honeycomb structure design is optimized, the problem of rotor jamming caused by too small labyrinth honeycomb clearance after the engine stops is solved, and the outfield execution rate of a certain type of engine is greatly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the technical solutions provided by this application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application.

[0028] Figure 1 It is a schematic diagram of the overall process of this application;

[0029] Figure 2 Schematic diagram of the labyrinth seal structure of the engine in this application;

[0030] Figure 3 High-energy X-ray measurement imaging effect diagram of this application;

[0031] Figure 4 Schematic diagram of the relative positions of the labyrinth and the honeycomb under different states of this application;

[0032] Figure 5 Schematic diagram of the honeycomb wear scar morphology result measured by high-energy X-ray of this application;

[0033] Figure 6 Schematic diagram of the honeycomb wear scar morphology measured by the closing paste of this application;

[0034] Figure 7 Schematic diagram of the actual deformation result of the honeycomb structure of this application;

[0035] Figure 8 Schematic diagram of the high-energy X-ray measurement result of this application;

[0036] Figure 9 Schematic diagram of the measurement result of the closing paste of this application;

[0037] Figure 10 Schematic diagram of the comparison of the honeycomb wear scar morphology before and after correction of this application.

[0038] 1. Wear scar contour; 2. First line; 3. Second line; 4. Third line; 5. Honeycomb structure; 6. Labyrinth. Detailed implementation manners

[0039] 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 with reference to the accompanying drawings in the embodiments of this application.

[0040] A data correction method for obtaining the labyrinth-honeycomb gap using high-energy X-rays, taking the labyrinth seal structure at one location of a certain type of engine as an example, specifically illustrates the verification of the accuracy of this method.

[0041] It includes the following steps:

[0042] Step S100, measure the labyrinth-honeycomb gap by high-energy X-rays, obtain the gap data of the labyrinth seal structures at multiple locations based on the high-energy X-ray measurement results, and obtain the movement trajectory of the labyrinth relative to the honeycomb and the measured gap results;

[0043] For the labyrinth-honeycomb structure 5 of a certain type of engine measured as Figure 2 shown, the imaging effect of the labyrinth-honeycomb structure 5 measured by high-energy X-rays is asFigure 3 As shown. By reading and analyzing the imaging effects at different times, the deformation law of the labyrinth seal structure of the labyrinth 6 is obtained. Then, through the data analysis of the relative position of the labyrinth 6 in the working state, such as Figure 4 As shown, the movement trajectory of the labyrinth 6 relative to the honeycomb and the measured clearance results are obtained, such as Figure 5 As shown.

[0044] Figure 5 In it, the 0 scale line of the vertical coordinate is equivalent to the working surface of the honeycomb. The data points above the 0 scale represent the rubbing between the labyrinth 6 and the honeycomb, and those below the 0 scale represent the clearance state between the labyrinth 6 and the honeycomb. Therefore, the area formed by the movement trajectory of the labyrinth 6 above the 0 scale line of the vertical coordinate and the 0 scale line represents the worn position of the honeycomb. From this, the honeycomb wear scar morphology, wear scar depth and width can be obtained, such as Figure 5 Shown by the thick solid wear scar contour line 1 at the top in

[0045] Step S200, measure the honeycomb wear scar morphology with putty. Based on the measurement results of the putty, obtain the honeycomb wear scar morphology and size data after multiple engine decompositions;

[0046] The wear scar image of the honeycomb structure 5 measured with putty is as Figure 6 Shown. A method combining a microscope and an image analyzer is used to measure and restore the size of the wear scar morphology obtained with the putty. The measurement accuracy of the image analyzer is (1.2 + 4L / 1000) μm.

[0047] By reading and analyzing the putty morphology at different seal structures, the actual deformation results of the honeycomb structure 5 are obtained as Figure 7 Shown. The curve in the figure is the actual deformation of the honeycomb structure 5. From this, the actual depth and width of the honeycomb wear scar can be obtained.

[0048] Step S300, apply two measurement methods of high-energy X-rays and putty on the same structure respectively to obtain the clearance results of the labyrinth honeycomb at each place and the size differences of the honeycomb wear scars in the radial and axial directions. Use the measurement results of the putty wear scars of the corresponding structure to calibrate the clearance results of the labyrinth (6) honeycomb measured by high-energy X-rays respectively, correct the measurement results, and determine the correction formula;

[0049] By comparing and analyzing the results of the two measurement methods of the same structure, the size differences of the honeycomb wear scars at each place in the radial and axial directions are obtained respectively. Then, use the measured results of the wear scars of the same structure to calibrate the data results obtained by X-rays to determine the preliminary correction formula for each structure.

[0050] Preferably, the method for correcting the measurement results of high-energy X-rays and putty specifically includes:

[0051] Set the radial and axial relative position values between the labyrinth 6 and the honeycomb to be A and B respectively; the radial and axial relative position values of the labyrinth 6 and the honeycomb after engine assembly are H0 and L0 respectively; the radial and axial relative position change values of the labyrinth 6 and the honeycomb during engine operation are H and L respectively; then we get:

[0052] A = H0 + H (1)

[0053] B = L0 + L (2)

[0054] During the test run, the radial and axial relative position change values of the labyrinth 6 and the honeycomb measured by high-energy X-ray are H' and L' respectively; then the correction targets are:

[0055] H = f'(H') (3)

[0056] L = g'(L') (4)

[0057] During the test run, the radial (depth) and axial (depth) values of the honeycomb wear marks measured by high-energy X-ray are ΔH and ΔL respectively; when H < H0, there is a clearance state between the labyrinth 6 and the honeycomb radially, so the corresponding wear mark depth and width are both 0; when H > H0, rubbing occurs between the labyrinth 6 and the honeycomb, and the labyrinth 6 will leave the rubbing depth and width on the honeycomb, so we have:

[0058] H < H0, ΔH = 0, ΔL = 0 (5)

[0059] H > H0, H' = ΔH + H0, L' = ΔL (6)

[0060] The radial (depth) and axial (depth) values of the honeycomb wear marks measured by the closing paste are Δh and Δl respectively; the depth and width measured in this state are the marks left by the labyrinth 6 rubbing against the honeycomb during the test run, which are the true values of the relative position change between the labyrinth 6 and the honeycomb during engine operation, so we have:

[0061] H = Δh + H0 (7)

[0062] L = Δl (8)

[0063] At the same time, it should be ΔH = Δh and ΔL = Δl.

[0064] Due to the existence of X-ray measurement and reading errors, the measurement results show different data for the two. Therefore, take the data measured by the closing paste as the true result and correct the measurement result of high-energy X-ray. Specifically:

[0065] ΔH' = f(Δh) (9)

[0066] ΔL' = g(Δl) (10)

[0067] Wherein, ΔH' and ΔL' are the radial and axial correction values of the honeycomb wear marks measured by high-energy X-rays.

[0068] Furthermore, establish the relationship between the high-energy X-ray measurement results H' / L' and H / L to obtain two different honeycomb morphologies of high-energy X-ray measurement and putty measurement; from formulas (6), (9), and (10), we get:

[0069] H' = H0 + f(Δh) (11)

[0070] L' = g(Δl) (12)

[0071] The measurement results are as Figure 8 and Figure 9 shown, where Figure 8 is the honeycomb morphology obtained from the high-energy X-ray measurement results, Figure 9 is the honeycomb morphology obtained from the putty measurement results.

[0072] Judging from the two measurement data results obtained, the honeycomb morphologies obtained from the high-energy X-ray measurement results and the putty measurement results are basically the same in terms of morphological characteristics, but there are differences in the width and depth of the wear marks. Considering that the axial width of the wear mark shows a linear change relationship and the general wear mark width does not exceed 4 mm, the specific correction method is as follows:

[0073] Taking the axial midline of the two morphologies as the reference point, equally divide the axis into 10 points, and correct the two measurement results of each sealing structure;

[0074] Then, use the least squares method, and utilize the radial and axial numerical values of the honeycomb wear marks measured by high-energy X-rays and putty to establish the relationship between the high-energy X-ray measurement results and the actual honeycomb wear mark measurement results, which is:

[0075] ΔH k = f(Δh k ) = aΔh k + b (13)

[0076] ΔL k = g(Δl k ) = cΔl k + d (14)

[0077] where k = 1, 2,..., 10 is the axial equal division point, and a, b, c, and d are the correction coefficients to be obtained.

[0078] Thus, obtain the relationship between the ray measurement results and the actual wear marks, specifically:

[0079] H k ' = H0 + aΔh k + b (15)

[0080] L k ' = cΔl k + d(16)

[0081] The corresponding relationships of different axial equal division points are shown in Table 1:

[0082] Table 1 Correction relationship between high-energy X-ray analysis data and measured data of honeycomb (k = 1, 2,..., 10)

[0083] k 1 2 …… k Δh Δh1 Δh2 …… Δhk ΔH ΔH1 ΔH2 …… ΔHK Δl Δl1 Δl2 …… Δlk ΔL ΔL1 ΔL2 …… ΔLK

[0084] Finally, the correction results of the honeycomb labyrinth 6 are fitted to obtain a correction formula. The specific steps are as follows:

[0085] Then, the correction results of the honeycomb of the labyrinth 6 at the 4th position of the engine are fitted, and the obtained correction formula is as follows:

[0086] H' = H0 + Δh / 2 + 0.025 (15)

[0087] L' = Δl / 2 + 0.008 (16)

[0088] From formulas (7), (8), (15), and (16), it can be obtained that:

[0089] H = 2H' - H0 - 0.05 (17)

[0090] L = 2L' - 0.016 (18)

[0091] Taking Figure 2 The measured data of the honeycomb structure 5 of the labyrinth 6 at the position are shown in Table 2. The wear scar morphologies before and after correction according to (15) and (16) are as Figure 10 shown. Among them, the first line 2 is the measured wear scar of the closing paste, the second line 3 is the X-ray wear scar, and the third line 4 is the correction result.

[0092] Table 2 Comparison between high-energy X-ray analysis data and measured data of honeycomb at a certain point

[0093] k 1 2 3 4 5 6 7 8 9 10 l 0.25 0.5 0.75 1.0 1.25 1.5 1.75 2 2.25 2.5 h 0.10 0.21 0.4 0.49 0.51 0.44 0.34 0.22 0.11 0 L 0.13 0.26 0.39 0.52 0.65 0.78 0.91 1.04 1.17 1.3 H 0.07 0.13 0.22 0.27 0.28 0.24 0.20 0.13 0.08 0

[0094] Step S400, propose and calibrate the validity of the correction formula through the analysis of the jamming problem after the engine stops and the test run verification.

[0095] As a specific implementation manner, through the analysis of the "jamming" problem after a certain engine stops and the test run verification, combined with the "jamming" performance before and after the optimization of the honeycomb clearance of the labyrinth 6, verify based on the correction results of the high-energy X-ray measurement data to complete the calibration of the validity of the correction formula.

[0096] There is a "sticking" problem in the high-pressure rotor of a certain type of engine after shutdown. High-energy X-rays are used to measure the change in the sealing gap of the labyrinth teeth 6 in the inner cavity of the high-pressure rotor, and the correction formula is applied to correct the measurement results. The corrected data results show that at a certain moment after shutdown, the radial gap of the labyrinth teeth 6 sealing structure in front of the combustion chamber is less than 0, and the rotor and stator are "stuck".

[0097] The engine was disassembled and the labyrinth teeth 6 honeycomb structure 5 with an increased gap was replaced. The test run results show that the "sticking" hours after shutdown were reduced from 3h to 4h to 0, and the problem was eliminated. At the same time, the high-energy X-ray measurement data shows that the radial gap at this place after shutdown is greater than 0. The accuracy of the corrected high-energy X-ray measurement data was verified.

[0098] In this application, the high-energy X-ray and putty are first used to measure the same labyrinth teeth 6 honeycomb structure 5 respectively to obtain the labyrinth teeth 6 honeycomb data of two different measurement methods, forming two honeycomb morphologies. Then, based on the high-energy X-ray measurement results, combined with the putty measurement results, the high-energy X-ray measurement results are corrected to obtain a correction coefficient, and the correction coefficient is applied to complete the correction and calibration of the high-energy X-ray measurement results; by combining the high-energy X-ray and putty measurements to correct the labyrinth teeth 6 honeycomb gap, the data accuracy and effectiveness are greatly improved.

[0099] Using the corrected data, the change law of the labyrinth teeth 6 honeycomb gap during the test run and after shutdown of a certain type of engine was obtained, the design of the labyrinth teeth 6 honeycomb structure 5 was optimized, and the problem of rotor sticking caused by too small a labyrinth teeth 6 honeycomb gap after engine shutdown was solved, greatly improving the outfield execution rate of a certain type of engine.

[0100] As described above, it is only the specific implementation manner of this application, but the protection scope of this application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in this application should be covered by the protection scope of this application. Therefore, the protection scope of this application should be subject to the protection scope of the claimed rights.

Claims

1. A data correction method for obtaining the clearance of labyrinth honeycomb by using high-energy X-rays, characterized in that, Including: Measuring the honeycomb clearance of the labyrinth (6) through high-energy X-rays, obtaining the clearance data of multiple labyrinth (6) sealing structures based on the high-energy X-ray measurement results, and obtaining the movement trajectory of the labyrinth (6) relative to the honeycomb and the measured clearance results; Measuring the honeycomb wear scar morphology through the closing compound, and obtaining the morphology and size data of multiple honeycomb wear scars after the engine is disassembled based on the closing compound measurement results; Applying two measurement methods of high-energy X-rays and closing compound respectively on the same structure to obtain the honeycomb clearance results of each labyrinth and the dimensional differences of the honeycomb wear scars in the radial and axial directions; Applying the measurement results of the closing compound wear scars of the corresponding structure to calibrate the honeycomb clearance results of each labyrinth (6) measured by high-energy X-rays respectively, correcting the measurement results, and determining the correction formula; Calibrating the effectiveness of the correction formula through the analysis of the jamming problem after the engine stops and the test run verification; The numerical values of the radial and axial relative positions of the labyrinth (6) and the honeycomb during the engine operation are H and L respectively; Taking the data measured by the closing compound as the true result and correcting the high-energy X-ray measurement result; Establishing the relationship between the high-energy X-ray measurement results H' / L' and H / L to obtain two different honeycomb morphologies measured by high-energy X-rays and the closing compound; Taking the axial midlines of the two morphologies as the reference points, equally dividing the axial direction into 10 points, and correcting the two measurement results of each sealing structure; using the radial and axial numerical values of the honeycomb wear scars measured by high-energy X-rays and the closing compound to establish the relationship between the high-energy X-ray measurement results and the actual honeycomb wear scar measurement results; Fitting the correction results of the honeycomb labyrinth (6) to obtain the correction formula.

2. The data correction method for obtaining the labyrinth honeycomb clearance by using high-energy X-rays as described in claim 1, wherein The method for correcting the measurement results includes: Setting the radial and axial relative position numerical values between the labyrinth (6) and the honeycomb as A and B respectively; the radial and axial relative position numerical values of the labyrinth (6) and the honeycomb after the engine is assembled are H0 and L0 respectively; the radial and axial relative position change numerical values of the labyrinth (6) and the honeycomb measured by high-energy X-rays are H' and L' respectively; the radial and axial numerical values of the honeycomb wear scars measured by high-energy X-rays are ΔH and ΔL respectively; the radial and axial numerical values of the honeycomb wear scars measured by the closing compound are Δh and Δl respectively; determining the true numerical values of the relative position changes of the labyrinth (6) honeycomb according to the numerical values measured by the closing compound and high-energy X-rays.

3. The data correction method for obtaining the labyrinth honeycomb clearance by using high-energy X-rays as described in claim 2, characterized in that, The expression of the true numerical value of the relative position change of the labyrinth (6) honeycomb is: H = Δh + H0 L = Δl.

4. The data correction method for obtaining the labyrinth honeycomb clearance by using high-energy X-rays according to claim 2, characterized in that, The correction expression of the high-energy X-ray measurement result is: ΔH' = f(Δh) ΔL' = g(Δl).

5. The data correction method for obtaining the labyrinth honeycomb clearance by using high-energy X-rays according to claim 2, wherein The expression of the high-energy X-ray measurement result H' / L' is: H' = H0 + f(Δh) L' = g(Δl).

6. The method for obtaining data correction of the labyrinth honeycomb clearance by using high-energy X-rays according to claim 2, characterized in that The relationship between the high-energy X-ray measurement result and the honeycomb wear scar is: H k ' = H0 + aΔh k + b L k ' = cΔl k + d where k = 1, 2,..., 10 is the axial equal division point, and a, b, c, d are the correction coefficients to be obtained.

7. The data correction method for obtaining the labyrinth honeycomb clearance by using high-energy X-rays as described in claim 2, characterized in that The correction formula is: H = 2H' - H0 - 0.05 L = 2L' - 0.016.

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