Method for assembling an aeroengine
By adjusting the position of parts relative to the turntable during the aero-engine assembly process using fitting curves and joint debugging algorithms, the problems of low efficiency and accuracy in runout detection were solved, enabling rapid benchmark adjustment and precise measurement, and reducing production costs.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AECC COMML AIRCRAFT ENGINE CO LTD
- Filing Date
- 2021-10-18
- Publication Date
- 2026-07-21
AI Technical Summary
In the existing technology, the efficiency and accuracy of runout detection during the assembly process of aero engines are low, resulting in errors in the measurement results.
By measuring the radial runout and end face runout data of the parts on the turntable, and using fitting curves and joint debugging algorithms to calculate and adjust the position of the parts relative to the turntable, rapid reference adjustment is achieved, reducing the coupling between modules and improving measurement accuracy.
It enables rapid benchmark adjustment during the detection of aero-engine runout, improving measurement accuracy and efficiency while reducing production costs.
Smart Images
Figure CN115993081B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aero-engines, and particularly relates to an assembly method for aero-engines. Background Technology
[0002] During the assembly of aero-engines, regardless of the condition of individual parts or components, stator assemblies or rotors, it is necessary to detect the runout of key positions relative to a reference surface to determine the condition of the parts or the assembly quality. The most commonly used equipment for this runout detection is a turntable. The part or component to be tested is placed on the turntable, and then the reference end face is adjusted to be perpendicular to the turntable's rotation axis, and the reference cylindrical surface is adjusted to coincide with the turntable's axis. This process is called reference adjustment. After reference adjustment, the runout of the surface to be tested is measured relative to the reference. It is worth noting that the result of the surface to be tested can be transferred to the reference by rotating the reference. However, if the reference adjustment is not within a certain range, extensive experiments have shown that the measurement result of the surface to be tested has a certain error. Therefore, using a turntable to adjust the radial runout of the reference so that the result is eccentric relative to the turntable axis, and adjusting the runout of the reference end face so that the perpendicularity of the result runout relative to the turntable axis is within a certain range, are crucial operations. The traditional method is to first adjust the end face runout so that the end face is basically perpendicular to the turntable's rotation axis, and then adjust the radial runout so that the radial eccentricity is basically coincident with the turntable's rotation axis. Each adjustment requires the turntable to rotate one revolution. For example, if the end face is adjusted to the power of n and then passes, the turntable will have rotated n revolutions. However, this method results in low measurement efficiency and low accuracy. Summary of the Invention
[0003] The technical problem to be solved by the present invention is to overcome the shortcomings of the existing technology in measuring the runout of the assembly relative to the reference surface, which is characterized by low efficiency and low accuracy, and to provide an assembly method for aero engines.
[0004] The present invention solves the above-mentioned technical problems through the following technical solution:
[0005] An assembly method for an aircraft engine includes the following steps:
[0006] Place the part to be tested on the turntable;
[0007] The runout of the reference datum of the part under test is measured using a measuring device to obtain radial runout data J and end face runout data T.
[0008] Based on the radial runout data J and the end face runout data T, adjust the position of the reference datum of the measured part relative to the turntable;
[0009] The fitted radial runout curve and the fitted end face curve are obtained based on the radial runout data J and the end face runout data T.
[0010] Based on the fitted radial runout curve and the fitted end face curve, a joint debugging algorithm is performed.
[0011] Based on the calculation results of the joint debugging algorithm, the optimal runout curve is obtained, and the radial runout and end face runout are adjusted at the same position until they are qualified.
[0012] In this technical solution, the aforementioned method enables rapid reference adjustment during engine runout detection. This method adjusts the end runout and radial runout of the reference end face simultaneously at the same angle during reference adjustment. An algorithm couples the adjustment amounts to obtain the final adjustment changes in radial and end runout, thereby improving the speed and accuracy of reference adjustment during engine runout detection. Furthermore, this method is applicable to runout detection of engines of different sizes, significantly reducing production and processing costs.
[0013] Preferably, the measuring device is an inductive sensor or a dial indicator.
[0014] Preferably, adjusting the position of the reference datum of the tested part relative to the turntable includes adjusting the eccentricity and tilt of the tested part relative to the turntable.
[0015] In this technical solution, adjusting the relative position of the measured part and the turntable helps to improve the reference measurement accuracy of the measured part and reduce the angular swing and axis tilt error of the rotating axis during the measurement process of the measured part.
[0016] Preferably, adjusting the eccentricity of the part under test relative to the turntable includes: adjusting the radial center of the reference datum of the part under test so that it coincides with the rotation axis of the turntable.
[0017] In this technical solution, adjusting the relative position of the measured part and the turntable helps to improve the reference measurement accuracy of the measured part and reduce the angular runout error of the rotation axis during the measurement of the measured part.
[0018] Preferably, adjusting the tilt of the part under test relative to the turntable includes: adjusting the end face normal of the reference datum of the part under test to be parallel to the rotation axis of the turntable.
[0019] In this technical solution, adjusting the relative position of the measured part and the turntable helps to improve the reference measurement accuracy of the measured part and reduce the axis tilt error of the rotating axis during the measurement of the measured part.
[0020] Preferably, obtaining the fitted runout curve based on the radial runout data J and the end face runout data T includes: obtaining the eccentric vector Ru based on the radial runout data J using the least squares method, and obtaining the plane normal vector Rv based on the end face runout data T.
[0021] In this technical solution, the rotation axes of the tested part and the turntable are made to coincide and parallel through the above-mentioned eccentricity and tilt adjustment. Therefore, fitting them can establish the connection between the tested part and the turntable, which is beneficial to further obtain the concentricity of the tested part relative to the aero-engine.
[0022] Preferably, the joint adjustment algorithm calculation based on the fitted radial runout curve and the fitted end face curve includes: coupling the eccentric vector Ru and the plane normal vector Rv to obtain the influence of the end face runout of the reference reference during the centering process and the influence of the radial runout of the reference reference during the tilting process.
[0023] In this technical solution, coupling the eccentric vector Ru and the plane normal vector Rv is to determine the tightness of their connection, minimizing the coupling between modules and thus improving module independence. Lower coupling indicates fewer connections between modules, better module independence, less mutual influence, and less impact on the operation of other modules. Modifications and maintenance of one module will not affect other modules. A modular structure design with low coupling reduces system complexity, making the system easier to understand, modify, and maintain.
[0024] Preferably, coupling the eccentric vector Ru and the plane normal vector Rv to obtain the influence of the end face runout of the reference datum during the centering process includes: during the centering process, projecting the eccentric vector Ru onto the end face of the reference datum to obtain the end face runout influence matrix T1.
[0025] Preferably, the effect of coupling the eccentric vector Ru and the plane normal vector Rv on the radial runout of the reference datum during the tilting process includes: during the tilting process, the radial runout effect matrix T2 is obtained by radially projecting the plane normal vector Rv onto the reference datum.
[0026] Preferably, the jump data is a vector set consisting of angle and jump.
[0027] The significant advantages of this invention are: this method enables rapid reference adjustment during engine runout detection. By simultaneously adjusting the end runout and radial runout of the reference end face at the same angle during the reference adjustment process, and using an algorithm to couple the adjustment amounts, the final adjustment changes in radial and end runout are obtained, thereby improving the speed and accuracy of reference adjustment during engine runout detection. Furthermore, this method is applicable to runout detection of engines of different sizes, significantly reducing production and processing costs. Attached Figure Description
[0028] Figure 1 This is a flowchart of the method in an embodiment of the present invention;
[0029] Figure 2 This is a schematic diagram of the assembly of the turntable and the part under test in an embodiment of the present invention;
[0030] Figure 3 This is the radial runout fluctuation curve after joint debugging in an embodiment of the present invention;
[0031] Figure 4 This is the fluctuation curve of the back end face during joint debugging in an embodiment of the present invention.
[0032] Explanation of reference numerals in the attached figures:
[0033] Turntable 1
[0034] Part 2 under test
[0035] Reference axis 3
[0036] Rotation axis 4
[0037] Radial reference 5 to be adjusted
[0038] Reference 6 of the end face to be adjusted
[0039] Radial runout data J of the reference datum of the tested part
[0040] The runout data T of the reference end face of the tested part
[0041] Eccentric vector Ru
[0042] Plane normal vector Rv Detailed Implementation
[0043] The present invention will be further illustrated by way of embodiments below, but the present invention is not limited to the scope of the embodiments described herein.
[0044] Example 1
[0045] This embodiment selects, as follows: Figure 2 The front journal of the aero-engine shown is used as the part under test to illustrate the technical solution. It should be noted that other structures in aero-engines can also be used as examples, and no specific limitation is made here.
[0046] like Figure 1 As shown, the assembly method for an aircraft engine includes the following steps:
[0047] Place the part to be tested, 2, on the turntable 1;
[0048] The runout of the reference datum of the part under test 2 is measured using a measuring device to obtain radial runout data J and end face runout data T; wherein, the runout data is a vector set composed of angle and runout; the reference datum includes the radial datum 5 to be adjusted and the end face datum 6 to be adjusted;
[0049] Based on the radial runout data J and the end face runout data T, adjust the position of the reference datum of the measured part relative to the turntable;
[0050] The fitted radial runout curve and the fitted end face curve are obtained based on the radial runout data J and the end face runout data T.
[0051] Based on the fitted radial runout curve and the fitted end face curve, a joint debugging algorithm is performed.
[0052] Based on the calculation results of the joint debugging algorithm, the optimal runout curve is obtained, and the radial runout and end face runout are adjusted at the same position until they are qualified.
[0053] It should be noted that the steps of adjusting the position of the reference datum of the tested part relative to the turntable based on the radial runout data J and the end face runout data T, and obtaining the fitted radial runout curve and the fitted end face curve based on the radial runout data J and the end face runout data T, do not have a time sequence, as long as they do not affect the subsequent joint debugging algorithm calculation.
[0054] The measuring device used in this embodiment can be an inductive sensor or a dial indicator.
[0055] In this embodiment, the relative positions of the turntable 1 and the part being measured 2 are as follows: Figure 2 As shown, adjusting the position of the reference datum of the tested part 2 relative to the turntable 1 includes adjusting the eccentricity and tilt of the tested part 2 relative to the turntable 1. Specifically:
[0056] Adjusting the eccentricity of the measured part 2 relative to the turntable 1 includes: adjusting the radial center (reference axis 3) of the radial reference 5 to be adjusted of the measured part 2 so that it coincides with the rotation axis 4 of the turntable 1. Adjusting the tilt of the measured part 2 relative to the turntable 1 includes: adjusting the end face normal (the line perpendicular to the end face) of the end face reference 6 to be adjusted of the measured part 2 to be parallel to the rotation axis 4 of the turntable 1. Adjusting the relative position of the measured part and the turntable helps to improve the reference measurement accuracy of the measured part and reduce the angular wobble and axis tilt error of the rotation axis during the measurement of the measured part.
[0057] The fitted runout curve obtained based on the radial runout data J and the end face runout data T includes: obtaining the eccentric vector Ru based on the radial runout data J using the least squares method, and obtaining the plane normal vector Rv based on the end face runout data T.
[0058] The advantages of using the least squares method are as follows: the least squares method finds the best function match for the data by minimizing the sum of squares of the errors; the least squares method can be used to easily obtain unknown data and minimize the sum of squares of the errors between the obtained data and the actual data.
[0059] Based on the fitted radial runout curve and the fitted end face curve, the joint adjustment algorithm calculation includes: coupling the eccentric vector Ru and the plane normal vector Rv to obtain the influence of the end face runout of the end face reference 6 to be adjusted during the centering process and the influence of the radial runout of the radial reference 5 to be adjusted during the tilting process. Specifically, as follows:
[0060] The effect of coupling the eccentric vector Ru and the plane normal vector Rv on the end face runout of the end face reference 6 during the centering process includes: during the centering process, the eccentric vector Ru is projected onto the end face of the reference reference to obtain the end face runout influence matrix T1.
[0061]
[0062] Where α1 is the angle between the axial vector generated by the radial jump projection and the rotation axis vector in the X-axis direction;
[0063] β1 is the angle between the axial vector generated by the radial jump projection and the rotation axis vector in the Y-axis direction;
[0064] dx1 represents the change in the x-coordinate of the axis during the eccentric transformation process;
[0065] dy1 represents the change in the y-coordinate of the eccentric transformation process.
[0066] The effect of coupling the eccentric vector Ru and the plane normal vector Rv on the radial runout of the radial reference 5 to be adjusted during the tilting process includes: during the tilting process, the radial runout effect matrix T2 is obtained by radially projecting the plane normal vector Rv onto the reference reference.
[0067]
[0068] In the formula, α2 is the angle between the axial vector generated by the end jump projection and the rotation axis vector in the X-axis direction;
[0069] β2 is the angle between the axial vector generated by the end jump projection and the rotation axis vector in the Y-axis direction;
[0070] dx2 represents the change in the x-coordinate of the plane during the transformation process;
[0071] dy2 represents the change in the y-coordinate of the plane during the transformation process.
[0072] The coupling of the eccentric vector Ru and the plane normal vector Rv is to determine the tightness of their connection, minimizing the coupling between modules and thus improving module independence. Lower coupling indicates fewer connections between modules, better module independence, less mutual influence, and less impact on the operation of other modules. Modifications and maintenance of one module will not affect other modules. A modular structure design with low coupling reduces system complexity, making the system easier to understand, modify, and maintain.
[0073] Using the above matrix to correct the jump, we obtain the optimal curve under ideal conditions, as shown below. Figure 3 and Figure 4 As shown, the bold lines represent the actual radial runout / actual end-face runout curve, while the non-bold lines represent the theoretical radial runout / theoretical end-face runout curve. Then, based on these curves, the end runout and radial runout are adjusted simultaneously at the same position until they are qualified.
[0074] To further accelerate the adjustment, the maximum adjustment amount can be projected along two directions to obtain the adjustment amounts for two specified angular phases. In this method, the two angular phases cannot be equal or complementary. Specifically, this projection method projects onto two vector directions. Let the amount to be adjusted be p, the angular phase to be adjusted be θ, and the available angular phases be α and β. Then, the amounts to be adjusted along the α and β directions are x and y, respectively. Solving the following system of equations will yield the adjustment amounts for the two angular phases.
[0075]
[0076] Where p is the amount to be adjusted, which can be extracted from the maximum difference before and after adjustment in the curve graph;
[0077] θ is the phase angle to be adjusted, which can be extracted from the maximum difference before and after adjustment in the curve graph;
[0078] α is the first angle in the specified direction;
[0079] β is the second angle in the specified direction;
[0080] x is the adjustment amount to be calculated at the angular phase α;
[0081] y is the adjustment amount to be calculated at the angular phase β.
[0082] It should be noted that the projection method in this embodiment is not limited to the one described above, as long as it facilitates the adjustment of the end jump and radial jump.
[0083] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.
Claims
1. An assembly method for an aircraft engine, characterized in that, Includes the following steps: Place the part to be tested on the turntable; The runout of the reference datum of the part under test is measured using a measuring device to obtain radial runout data J and end face runout data T. Based on the radial runout data J and the end face runout data T, adjust the position of the reference datum of the measured part relative to the turntable; The fitted radial runout curve and the fitted end face curve are obtained based on the radial runout data J and the end face runout data T. Based on the fitted radial runout curve and the fitted end face curve, a joint debugging algorithm is performed. Based on the calculation results of the joint debugging algorithm, the optimal runout curve is obtained, and the radial runout and end face runout are adjusted at the same position until they are qualified. in, The fitted runout curve obtained based on the radial runout data J and the end face runout data T includes: obtaining the eccentric vector Ru based on the radial runout data J using the least squares method, and obtaining the plane normal vector Rv based on the end face runout data T; The joint adjustment algorithm calculation based on the fitted radial runout curve and the fitted end face curve includes: coupling the eccentric vector Ru and the plane normal vector Rv to obtain the influence of the end face runout of the reference datum during the centering process and the influence of the radial runout of the reference datum during the tilting process.
2. The assembly method of the aero-engine as described in claim 1, characterized in that, The measuring device is an inductive sensor or a dial indicator.
3. The assembly method of the aero-engine as described in claim 1, characterized in that, Adjusting the position of the reference datum of the part under test relative to the turntable includes adjusting the eccentricity and tilt of the part under test relative to the turntable.
4. The assembly method of the aero-engine as described in claim 3, characterized in that, Adjusting the eccentricity of the part under test relative to the turntable includes: adjusting the radial center of the reference datum of the part under test so that it coincides with the rotation axis of the turntable.
5. The assembly method of an aero-engine as described in claim 3, characterized in that, Adjusting the tilt of the part under test relative to the turntable includes: adjusting the end face normal of the reference datum of the part under test to be parallel to the rotation axis of the turntable.
6. The assembly method of the aero-engine as described in claim 1, characterized in that, The effect of coupling the eccentric vector Ru and the plane normal vector Rv on the end face runout of the reference datum during the centering process includes: during the centering process, the eccentric vector Ru is projected onto the end face of the reference datum to obtain the end face runout influence matrix T1.
7. The assembly method of an aero-engine as described in claim 1, characterized in that, The effect of coupling the eccentric vector Ru and the plane normal vector Rv on the radial runout of the reference datum during the tilting process includes: during the tilting process, the radial runout effect matrix T2 is obtained by radially projecting the plane normal vector Rv onto the reference datum.
8. The assembly method of an aero-engine as described in claim 1, characterized in that, The jump data is a vector set composed of angle and jump.