An assembly method for an aeroengine

Abstract

The present invention discloses an assembly method for an aero-engine, comprising the following steps: in the state of the high-pressure compressor rotor unit body, while measuring the runout of the front shaft diameter reference, measuring the runout of the center of the labyrinth disc and the runout of the turntable corresponding to the last-stage rotor of the high-pressure compressor, and then assembling the high-pressure turbine rotor and the high-pressure compressor rotor to the stator casing to complete the overall machine assembly. While measuring the runout of the rear shaft radial reference D, measuring the runout of the center of the labyrinth disc and the runout of the turntable corresponding to the last-stage rotor of the high-pressure compressor again. By reconstructing the axis of the rotor inner cavity, the concentricity of the center of the labyrinth disc of the engine relative to the front and rear references is finally obtained. The present invention is beneficial to solving the problems of large angular swing and inclination error of the rotation axis, and improving the measurement accuracy of the concentricity of the center of the labyrinth disc.

Description

Technical Field

[0001] The present invention belongs to the field of aero-engines, and particularly relates to an assembly method for an aero-engine. Background Art

[0002] During the general assembly process of an aero-engine, after the high-pressure turbine rotor and the high-pressure compressor rotor are assembled to the stator casing, it is necessary to measure the runout of the labyrinth disc center with the front journal diameter and the rear journal diameter supports as the reference, so as to obtain the concentricity of the labyrinth disc center relative to the front and rear references. As Figure 1 shown, the front journal diameter reference is C, and the rear journal diameter reference is D. The purpose is to analyze the overall unbalance of the high-pressure rotor and the vibration analysis, so as to improve the assembly quality of the engine rotor. However, during the measurement process, the support state of the high-pressure rotor is in a vertical state. Due to the influence of the angular swing of the two supports of the front journal diameter reference C and the rear journal diameter D and the axis inclination state, the rotating shaft of the high-pressure compressor rotor cannot rotate along the fixed rotating shaft. That is to say, the fixed rotation is not in a completely vertical state, and the rotation axis is not the rotating shaft in the engine working state.

[0003] The traditional method for measuring the concentricity of the labyrinth disc center in this field is to fix the front journal diameter reference C with a bearing and fix the rear journal diameter reference D with a roller, directly measure the runout of the labyrinth disc, and calculate the eccentric vector through the runout of the labyrinth disc as the concentricity of the labyrinth disc center relative to the front and rear references. Therefore, this method cannot obtain the accurate concentricity of the labyrinth disc center relative to the front and rear references, and the overall measurement structure will cause significant errors in the measurement results. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to overcome the defect that the accurate concentricity of the labyrinth disc center relative to the front and rear journal diameter references cannot be obtained in the prior art, and the overall measurement structure will cause significant errors in the measurement results, and provide an assembly method for an aero-engine.

[0005] The present invention solves the above technical problem through the following technical solutions:

[0006] An assembly method for an aero-engine includes the following steps:

[0007] S1. Measure the runout of the high-pressure compressor rotor state alone, and simultaneously obtain the radial runout data Rc of the front journal diameter reference, the radial runout data Rb of the reference cylinder surface of the first reference component, and the radial runout data Rx of the reference cylinder surface of the second reference component. Among them, the first reference component and the second reference component are components on the high-pressure compressor rotor, and the reference cylinder surfaces of the first reference component and the second reference component are coaxial with the high-pressure compressor rotor;

[0008] S2. Assemble the high-pressure turbine rotor and the high-pressure compressor rotor to the stator casing to complete the assembly of the whole machine, measure the runout of the whole machine assembly, and simultaneously obtain the radial runout data Rd of the rear shaft diameter reference, the radial runout data Rbv of the reference cylinder surface of the first reference component, and the radial runout data Rxv of the reference cylinder surface of the second reference component;

[0009] S3. Combine the runout data obtained by separately measuring the high-pressure compressor rotor unit and the runout data obtained by measuring the whole machine assembly to obtain a fitted axis based on the front shaft diameter reference and the rear shaft diameter reference;

[0010] S4. Obtain the concentricity data of the labyrinth disc according to the fitted axis;

[0011] S5. If the concentricity data of the labyrinth disc does not meet the standard, perform installation adjustment and return to execute the steps of S1 - S4 until the concentricity data of the labyrinth disc meets the standard.

[0012] In this technical solution, the runout of the reference cylinder surfaces of the front and rear shaft diameter references and the reference components is beneficial to improving the measurement accuracy of the concentricity of the labyrinth disc center, and reducing the angular swing of the rotation axis and the axis inclination error during the measurement of the labyrinth disc center.

[0013] Preferably, the reference cylinder surface of the first reference component in S1 and S2 is the center of the labyrinth disc.

[0014] In this technical solution, since the purpose of the present invention is to measure the concentricity of the labyrinth disc center relative to the front and rear shaft diameter references, the center of the labyrinth disc is selected as the reference cylinder surface of the first reference component in order to directly establish a connection with the front and rear shaft diameter references and improve the measurement accuracy of the concentricity of the labyrinth disc center.

[0015] Preferably, the reference cylinder surface of the second reference component in S1 and S2 is the rotor disc corresponding to a certain stage of rotor blades of the high-pressure compressor.

[0016] In this technical solution, the rotor disc corresponding to a certain stage of rotor blades of the high-pressure compressor is selected as the reference cylinder surface of the second reference component because it and the labyrinth disc both belong to the rotating discs on the high-pressure compressor rotor, ensuring that they are coaxial and guaranteeing the accuracy of subsequent measurements.

[0017] Preferably, the rotor disc corresponding to the certain stage of rotor blades is the rotor disc corresponding to the last stage of rotor blades.

[0018] In this technical solution, the rotor disc corresponding to the last stage of rotor blades is selected as the reference cylinder surface of the second reference component because it is the closest to the labyrinth disc, ensuring the concentricity accuracy between the labyrinth disc and the rotor disc corresponding to the last stage of rotor blades and guaranteeing the accuracy of subsequent measurements.

[0019] Preferably, in S3, the steps of combining the runout data obtained by separately measuring the high-pressure compressor rotor unit and the runout data obtained by measuring the overall machine assembly include: establishing a first coordinate system based on Rb and Rx, obtaining the center coordinates of the front journal diameter reference based on Rc and corresponding them to the first coordinate system; establishing a second coordinate system based on Rbv and Rxv, and obtaining the center coordinates of the rear journal diameter reference based on Rd and corresponding them to the second coordinate system.

[0020] In this technical solution, by establishing a coordinate system to simulate the relative positions of the high-pressure compressor rotor and the high-pressure turbine rotor in the stator casing of an aeroengine, the positions of the front journal diameter reference and the rear journal diameter reference on the coordinate axes are further obtained, which is convenient for fitting.

[0021] Preferably, in S3, obtaining the fitting axis based on the front journal diameter reference and the rear journal diameter reference includes: making the first coordinate system and the second coordinate system coincide, and fitting the centers of the front journal diameter reference and the rear journal diameter reference to obtain the fitting axis.

[0022] In this technical solution, since the first coordinate system and the second coordinate system coincide, fitting them can establish the connection between the front journal diameter reference and the rear journal diameter reference, which is beneficial to further obtaining the concentricity of the labyrinth disc center relative to the front journal diameter reference and the rear journal diameter reference.

[0023] Preferably, the labyrinth disc concentricity data is the concentricity amplitude value and the angular phase of the center of the labyrinth disc relative to the fitting axis.

[0024] Preferably, establishing a first coordinate system based on Rb and Rx includes:

[0025] Fitting Rb to obtain its center, fitting Rx to obtain its center, using the vector connecting the centers of Rb and Rx as the first axis of the first coordinate system, using the perpendicular line from the starting point of the runout data to the first axis as the second axis of the first coordinate system, and establishing the first coordinate system with the center of Rb as the origin of the coordinate system.

[0026] Preferably, establishing a second coordinate system based on Rbv and Rxv includes:

[0027] Fitting Rbv to obtain its center, fitting Rxv to obtain its center, using the vector connecting the centers of Rbv and Rv as the first axis of the second coordinate system, using the perpendicular line from the starting point of the runout data to the first axis as the second axis of the second coordinate system, and establishing the second coordinate system with the center of Rbv as the origin of the coordinate system.

[0028] Preferably, the runout data is a vector set composed of angles and runouts.

[0029] The positive and progressive effects of the present invention are as follows: By separately measuring the runout of the high-pressure compressor rotor and the runout during the overall machine assembly, the relative relationship between the front journal reference and the rear journal reference is obtained. By reconstructing the axis of the rotor inner cavity, the concentricity of the labyrinth disc center relative to the front and rear references is finally obtained. This method solves the problems of large angular swing of the rotation axis and large axis inclination error during the measurement of the labyrinth disc center, and improves the accuracy of the concentricity of the labyrinth disc center relative to the front and rear references. At the same time, during the assembly process, by measuring, calculating, and adjusting, the problem of high cost of using high-precision equipment is avoided. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of the runout position structure;

[0031] Figure 2 It is the runout measurement of the high-pressure compressor rotor state;

[0032] Figure 3 It is the runout measurement of the overall machine assembly state;

[0033] Figure 4 It is a schematic diagram of the first coordinate system and the second coordinate system and a schematic diagram of the concentricity amplitude of the labyrinth disc center relative to the fitted axis;

[0034] Figure 5 It is the concentricity angular phase of the labyrinth disc center relative to the fitted axis.

[0035] DESCRIPTION OF THE REFERENCE NUMERALS:

[0036] High-pressure compressor rotor 1

[0037] High-pressure turbine rotor 2

[0038] Stator casing 3

[0039] Front journal reference C

[0040] Rear journal reference D

[0041] Radial runout data Rb (Rbv) of the reference cylindrical surface of the first reference component

[0042] Radial runout data Rx (Rxv) of the reference cylindrical surface of the second reference component

[0043] Radial runout data Rc of the front journal reference

[0044] Radial runout data Rd of the rear journal reference DETAILED DESCRIPTION OF THE EMBODIMENTS

[0045] The present invention will be further described below by way of examples, but the present invention is not limited to the scope of the described examples.

[0046] The present invention provides an assembly method for an aeroengine, comprising the following steps:

[0047] S1. As shown in Figure 2 , separately measure the state runout of the high-pressure compressor rotor 1, and simultaneously obtain the radial runout data Rc of the front shaft diameter reference C, the radial runout data Rb of the reference cylinder surface of the first reference component, and the Rx of the reference cylinder surface of the second reference component. Wherein, the first reference component and the second reference component are components on the high-pressure compressor rotor, and the reference cylinder surfaces of the first reference component and the second reference component are coaxial with the high-pressure compressor rotor 1; the runout data is a vector set composed of angles and runouts.

[0048] S2. As shown in Figure 3 , assemble the high-pressure turbine rotor 2 and the high-pressure compressor rotor 1 to the stator casing 3 to complete the overall engine assembly, measure the runout of the overall engine assembly, and simultaneously obtain the radial runout data Rd of the rear shaft diameter reference D, the radial runout data Rbv of the reference cylinder surface of the first reference component, and the Rxv of the reference cylinder surface of the second reference component;

[0049] S3. Combine the runout data obtained by separately measuring the high-pressure compressor rotor and the runout data obtained by measuring the overall engine assembly to obtain a fitted axis based on the front shaft diameter reference and the rear shaft diameter reference;

[0050] S4. Obtain the concentricity data of the labyrinth disc according to the fitted axis;

[0051] S5. If the concentricity data of the labyrinth disc does not meet the standard, perform installation adjustment and return to execute steps S1 - S4 until the concentricity data of the labyrinth disc meets the standard.

[0052] Wherein, the reference cylinder surface of the first reference component in S1 and S2 is the center of the labyrinth disc, and the reference cylinder surface of the second reference component is the rotor disc corresponding to the last-stage rotor blade of the high-pressure compressor rotor.

[0053] It should be noted that the reference cylinder surface of the first reference component and the reference cylinder surface of the second reference component in this embodiment may also be the reference cylinder surfaces of any two reference components on the high-pressure compressor rotor, and no specific limitation is made thereto, as long as they are coaxial with the high-pressure compressor rotor.

[0054] Since the purpose of the present invention is to measure the concentricity of the center of the labyrinth disc relative to the front and rear shaft diameter references, therefore, in this embodiment, selecting the center of the labyrinth disc as the reference cylinder surface of the first reference component is to directly establish a connection with the front and rear shaft diameter references and improve the measurement accuracy of the concentricity of the center of the labyrinth disc. And selecting the rotor disc corresponding to the last-stage rotor blade as the reference cylinder surface of the second reference component is because it is the closest to the labyrinth disc, and it is also to ensure the concentricity accuracy between the labyrinth disc and the rotor disc corresponding to the last-stage rotor blade, thereby ensuring the accuracy of subsequent measurements.

[0055] In S3, the steps of combining the runout data obtained by separately measuring the high-pressure compressor rotor unit and the runout data obtained by measuring the whole machine assembly include:

[0056] 1. Based on Rb and Rx, establish a first coordinate system. Based on the runout data Rc of the front journal datum C, obtain the center coordinates of the front journal datum C and map them to the first coordinate system.

[0057] Specifically, the definition of the first coordinate system is as shown by XYZ in Figure 4 . Fit the radial runout data Rb of the labyrinth disc center to obtain its center Ob, fit the radial runout data of the rotor disc center Rx corresponding to the last stage rotor of the high-pressure compressor to obtain its center Ox. Take the vector connecting the centers Ob and Ox as the Z-axis of the first coordinate system, take the perpendicular line from the starting point of the runout data to the Z-axis as the X-axis of the first coordinate system, and establish a first coordinate system O-XYZ with the center Ob as the origin of the coordinate system. Fit the runout data Rc of the front journal datum C to obtain the center Ob of the front journal datum C, and then convert the coordinate data of the center Oc to the O-XYZ coordinate system to obtain the center coordinates of the front journal datum C as (Xc, Yc, Zc).

[0058] 2. Based on Rbv and Rxv, establish a second coordinate system. Based on the runout data Rd of the rear journal datum D, obtain the center coordinates of the rear journal datum Od and map them to the second coordinate system.

[0059] Specifically, the definition of the second coordinate system is as shown by UVW in Figure 4 . Use the runout data during the whole machine assembly process to fit the runout data Rbv of the labyrinth disc to obtain its center Obv, fit the runout data Rxv of the rotor disc corresponding to the last stage rotor of the high-pressure compressor to obtain its center Oxv. Take the vector connecting the centers Obv and Oxv as the W-axis of the coordinate system, take the perpendicular line from the starting point of the runout data to the W-axis as the U-axis, and establish a coordinate system O-UVW with Obv as the center. It should be noted that at this time, there is no assembly change in the labyrinth disc and the rotor disc corresponding to the last stage rotor before and after assembly, and at this time, the coordinate system O-UVW coincides with the coordinate system O-XYZ.

[0060] Furthermore, fit the center Oc of the front journal datum C and the center Od of the rear journal datum C to obtain the fitted axis (i.e., the rotation axis). Further, the concentricity amplitude p of the labyrinth disc center relative to the fitted axis and the eccentricity angle α of the concentricity relative to the front and rear references can be obtained according to the following formula.

[0061]

[0062] Combine Figure 4 and Figure 5It can be obtained that in the formula, (Xc - Xd, Yc - Yd, Zc - Zd) is the center coordinate of the front shaft diameter reference C minus the center coordinate of the rear shaft diameter reference, (Xc, Yc, Zc) is the coordinate of the center of the reference C in the coordinate system O-UVW; (Xd, Yd, Zd) is the coordinate of the center of the reference D in the coordinate system O-UVW.

[0063] It should be noted that in the present invention, a rectangular coordinate system (i.e., the first and second coordinate systems) is established to simulate the relative positions of the high-pressure compressor rotor and the high-pressure turbine rotor in the stator casing, so as to establish the relative relationship between the front shaft diameter reference and the rear shaft diameter reference, obtain the assignment, and then convert the center of the front shaft diameter reference and the center of the rear shaft diameter reference in the rectangular coordinate system into polar coordinates in the polar coordinate system to further obtain the relationship between the polar radius and the polar angle, that is, R(α), and obtain the angular phase. However, the present invention is not limited thereto, as long as the concentricity amplitude and the angular phase of the labyrinth disc center relative to the front and rear shaft diameter references can be obtained.

[0064] Although the specific embodiments of the present invention have been described above, those skilled in the art should understand that this is only an example, and the protection scope of the present invention is defined by the appended claims. Without departing from the principles and essence of the present invention, those skilled in the art can make various changes or modifications to these embodiments, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. An assembly method for an aeroengine, characterized in that, it includes the following steps: S1. Independently measure the state runout of the high-pressure compressor rotor, and simultaneously obtain the radial runout data Rc of the front journal reference, the radial runout data Rb of the reference cylinder surface of the first reference component, and the radial runout data Rx of the reference cylinder surface of the second reference component. Among them, the first reference component and the second reference component are components on the high-pressure compressor rotor, and the reference cylinder surfaces of the first reference component and the second reference component are coaxial with the high-pressure compressor rotor; S2. Assemble the high-pressure turbine rotor and the high-pressure compressor rotor to the stator casing to complete the overall engine assembly, measure the runout of the overall engine assembly, and simultaneously obtain the radial runout data Rd of the rear journal reference, the radial runout data Rbv of the reference cylinder surface of the first reference component, and the radial runout data Rxv of the reference cylinder surface of the second reference component; S3. Combine the runout data obtained by independently measuring the high-pressure compressor rotor and the runout data obtained by measuring the overall engine assembly to obtain a fitted axis based on the front journal reference and the rear journal reference, including establishing a first coordinate system based on Rb and Rx, obtaining the center coordinates of the front journal reference based on Rc and corresponding them to the first coordinate system; establishing a second coordinate system based on Rbv and Rxv, obtaining the center coordinates of the rear journal reference based on Rd and corresponding them to the second coordinate system, and fitting the center of the front journal reference and the center of the rear journal reference to obtain the fitted axis; S4. Obtain the concentricity data of the labyrinth disc according to the fitted axis; S5. If the concentricity data of the labyrinth disc does not meet the standard, perform installation adjustment and return to execute steps S1 - S4 until the concentricity data of the labyrinth disc meets the standard.

2. The assembly method for an aeroengine according to claim 1, characterized in that, the reference cylinder surface of the first reference component in S1 and S2 is the center of the labyrinth disc.

3. The assembly method for an aeroengine according to any one of claims 1 or 2, characterized in that, the reference cylinder surface of the second reference component in S1 and S2 is the rotor disc corresponding to a certain stage of rotor blades of the high-pressure compressor rotor.

4. The assembly method for an aeroengine according to claim 3, characterized in that, the rotor disc corresponding to a certain stage of rotor blades is the rotor disc corresponding to the last stage of rotor blades.

5. The assembly method for an aeroengine according to claim 1, characterized in that, in S3, make the first coordinate system and the second coordinate system coincide, fit the center of the front journal reference and the center of the rear journal reference to obtain the fitted axis.

6. The assembly method for an aeroengine according to claim 1, characterized in that, the concentricity data of the labyrinth disc is the concentricity amplitude value and phase angle of the center of the labyrinth disc relative to the fitted axis.

7. The method according to claim 1, characterized in that, establishing a first coordinate system based on Rb and Rx includes: Fit Rb to obtain its center, fit Rx to obtain its center. Use the vector connecting the centers of Rb and Rx as the first axis of the first coordinate system, use the perpendicular line from the starting point of the runout data to the first axis as the second axis of the first coordinate system, and establish the first coordinate system with the center of Rb as the origin of the coordinate system.

8. The assembly method of an aeroengine according to claim 1, characterized in that establishing a second coordinate system based on Rbv and Rxv includes: Fit Rbv to obtain its center, fit Rxv to obtain its center. Use the vector connecting the centers of Rbv and Rxv as the first axis of the second coordinate system, use the perpendicular line from the starting point of the runout data to the first axis as the second axis of the second coordinate system, and establish the second coordinate system with the center of Rbv as the origin of the coordinate system.

9. The assembly method of an aeroengine according to claim 1, characterized in that the runout data is a vector set composed of angles and runouts.

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