Progressive balancing method for high pressure compressor rotor drum with multiple correction surfaces of aero-engine

Abstract

This invention discloses a progressive balancing method for the multi-calibration surface of a high-pressure compressor rotor drum in an aero-engine. The method includes the following steps: hoisting the high-pressure rotor onto a dynamic balancing machine, assembling a counterweight, and measuring the initial imbalance; removing the counterweight and measuring the real-time imbalance again; balancing the difference between the real-time imbalance of the third-level and fourth-level calibration surfaces of the drum and the values ​​of the real-time imbalance of the fourth-level and third-level calibration surfaces of the drum to a value less than or equal to 50 g·mm; removing the high-pressure rotor and assembling the rotor disc and shaft; balancing the values ​​of the real-time imbalance of the rotor front-end calibration surface and the rotor rear-end calibration surface to a value less than or equal to 10 g·mm. This invention eliminates the unbalanced torque inside the rotor step by step, reducing the bending deformation of the flexible rotor under unbalanced excitation at high speeds.

Description

Technical Field

[0001] This invention belongs to the field of rotor drum correction surface balancing technology, specifically relating to a multi-correction surface progressive balancing method for the rotor drum of a high-pressure compressor in an aero-engine. Background Technology

[0002] Aero-engine vibration failure refers to abnormal vibration phenomena that occur during the operation of an aero-engine. These failures not only affect the normal operation of the engine but may also seriously impact its lifespan and flight safety. The causes of vibration failures are varied, mainly including rotor imbalance, rotor-stator rubbing, misalignment, thermal bending, and blade vibration.

[0003] The existing rotor balancing method adopts the "A Step-by-Step Balancing Method for Enhanced Disc Compressor Rotors" with application number CN202311036176.8, which includes the following steps:

[0004] S101: Perform static balancing on the shaft to within the allowable range, and mark the mass point of the shaft;

[0005] S102: Using the mass point obtained in S101 as a reference, install the intermediate stage impeller on the shaft;

[0006] S103: Perform static balance adjustment on the intermediate rotor obtained in S102, adjust it to the allowable range and mark the mass point;

[0007] S104: Based on the mass point obtained in S103, install two impellers on both sides of the shaft along the axial direction of the intermediate stage impeller on the shaft.

[0008] S105: Perform dynamic balancing on the final intermediate rotor, adjust it to the allowable range, and mark the mass points;

[0009] S106: Based on the final mass point, install two impellers on both sides of the shaft along the axial direction of the intermediate stage impeller;

[0010] S107: Repeat S105-S106 until all impellers are installed, and adjust the dynamic balance of the compressor rotor to the allowable range.

[0011] Because the rotor of a certain type of aero-engine high-pressure compressor is an elastic flexible rotor and has the property of crossing multiple critical speeds during operation, the balance of the installed rotor is poor when the above method is used. Summary of the Invention

[0012] In order to solve the problem of poor rotor balance in the installation and balancing of elastic flexible rotors by existing methods, this invention proposes a multi-correction surface progressive balancing method for the drum of a high-pressure compressor rotor of an aero-engine.

[0013] The objective of this invention is achieved through the following technical solution:

[0014] This invention discloses a multi-correction surface progressive balancing method for the rotor drum of a high-pressure compressor in an aero-engine, which includes the following steps:

[0015] The front journal end of the high-pressure rotor is fixed with a fixed bracket, and the six-stage rotor is fixed on the pressure plate of the fixed bracket.

[0016] A balancing device is installed on the high-pressure rotor;

[0017] After hoisting the high-pressure rotor onto the dynamic balancing machine, the factory counterweights are installed on each calibration surface. Then, the initial imbalance of the third-level calibration surface, the fourth-level calibration surface, the first-level calibration surface, and the sixth-level calibration surface of the drum is measured.

[0018] After removing the factory counterweights from each calibration surface in situ and assembling them, the real-time imbalance of the third-level calibration surface, the fourth-level calibration surface, the first-level calibration surface, and the sixth-level calibration surface of the drum is measured again.

[0019] Based on the phase difference of the real-time imbalance of the third-level and fourth-level correction surfaces of the drum and the magnitude of the real-time imbalance of the fourth-level and third-level correction surfaces of the drum, the difference between the real-time imbalance of the third-level and fourth-level correction surfaces of the drum or the first-level and sixth-level correction surfaces of the drum and its corresponding initial imbalance is balanced to less than or equal to 50 g•mm.

[0020] Remove the high-pressure rotor from the balancing machine and assemble the rotor disc and shaft onto the high-pressure rotor;

[0021] The high-pressure rotor is hoisted onto the dynamic balancing machine, and the real-time imbalance values ​​of the rotor front end correction surface and the rotor rear end correction surface are balanced to less than or equal to 10 g•mm.

[0022] The beneficial effects of this invention are:

[0023] This invention uses a multi-correction surface progressive balancing method to eliminate unbalanced torque inside the rotor step by step. This can significantly reduce the degree of bending deformation of the flexible rotor under unbalanced excitation at high speeds, thereby reducing vibration amplitude and eliminating vibration faults. Ordinary low-speed dynamic balancing equipment can achieve the same effect as high-speed dynamic balancing equipment. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the fixed support structure;

[0026] Figure 2 This is a schematic diagram of the balancing device.

[0027] Figure 3 This is a schematic diagram of the high-voltage rotor. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0029] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0030] It should be noted that, unless otherwise specified, the embodiments and features described in this invention can be combined with each other.

[0031] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0032] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this invention is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0033] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0034] This invention discloses a multi-correction surface progressive balancing method for the rotor drum of a high-pressure compressor in an aero-engine. The method includes steps S11 to S17. It should be noted that the step identifiers in this solution are only for the convenience of describing the method and do not constitute a limitation on the order of steps. The order of each step is based on its verbal description and the sequential connection of each signal.

[0035] Step S11: Fix the front journal end of the high-pressure rotor with a fixed bracket, and fix the six-stage rotor on the pressure plate of the fixed bracket.

[0036] A schematic diagram of the high-voltage rotor is shown below. Figure 3 As shown, when this step is fixed, only the first-stage correction surface A of the drum, the sixth-stage correction surface of the drum, and the rotor between the two are assembled on the high-pressure rotor, that is, only the first-stage rotor, second-stage rotor, third-stage rotor, fourth-stage rotor, fifth-stage rotor, and sixth-stage rotor are assembled. One end of the first-stage rotor is the front journal end.

[0037] Specifically, the structure of the fixed bracket is as follows: Figure 3 As shown, it includes a support frame 11, a high-pressure rotor fixture rotatably mounted on the support frame 11, and a control component 12 for controlling the rotation of the high-pressure rotor fixture; the high-pressure rotor fixture includes at least two connecting rods 13, a support rod 14 fixed to one end of the connecting rod 13 and placed on the same plane for supporting the front axle journal end, a fixing plate 16 fixed to the other end of the connecting rod 13, a pressure plate 15 placed between the support rod 14 and the fixing plate 16, and an adjusting screw 17 connected between the pressure plate 15 and the fixing plate 16 for adjusting the distance between the support rod 14 and the pressure plate 15.

[0038] To facilitate movement and operation, the support frame 11 is equipped with casters 18 at its bottom.

[0039] To enhance structural stability and simplify the structure, there are three connecting rods 13 arranged in parallel to each other, with two connecting rods 13 rotatably mounted on the support frame 11.

[0040] For ease of operation, such as Figure 1 As shown, the pressure plate 15 is semi-circular.

[0041] It should be noted that, Figure 1 Component 2 in the image is a sample of the installation example and is not a high-pressure rotor.

[0042] The fixed bracket has a simple structure. When fixing, the high-pressure rotor is placed into the fixed bracket from one end of the opening of the pressure plate 15, and its front axle journal end is placed on the support rod 14. Then, by rotating the adjusting screw 17, the pressure plate 15 can be pressed onto the end face of the six-stage rotor to fix the high-pressure rotor.

[0043] Step S12: Assemble a balancing device on the high-pressure rotor.

[0044] Specifically, the first step is to operate the fixed bracket, operate the control component 12 to rotate the high-pressure rotor fixture so that the front journal end of the high-pressure rotor is upward, and assemble the process bearing at the front journal end; then assemble the balancing device on the process bearing, operate the fixed bracket, that is, rotate the high-pressure rotor fixture so that the sixth-stage rotor end is upward; finally, heat the sixth-stage positioning plate of the balancing device and fix the sixth-stage positioning plate and the sixth-stage rotor.

[0045] The structure of the balancing device is as follows: Figure 2 As shown, it includes a balancing device body 6, a six-stage positioning plate 7 disposed at one end of the balancing device body 6, and a flange positioning plate 5 disposed at the other end of the balancing device body 6.

[0046] The balancing device is connected and fixed to the outer steel sleeve of the process bearing via flange positioning plate 5.

[0047] Step S13: After hoisting the high-pressure rotor onto the dynamic balancing machine, install the factory counterweights from the last maintenance onto each calibration surface, and then measure the initial imbalance of the drum cylinder third-level calibration surface 83, drum cylinder fourth-level calibration surface 84, drum cylinder first-level calibration surface 82, and drum cylinder sixth-level calibration surface 85.

[0048] Step S14: After removing the factory counterweights from each calibration surface in situ, measure the initial imbalance of the third-level calibration surface, the fourth-level calibration surface, the first-level calibration surface, and the sixth-level calibration surface of the drum again.

[0049] In this step, the factory counterweight is the same as the factory counterweight used during the last maintenance, which is the standard counterweight.

[0050] Step S15: Based on the phase difference of the real-time imbalance of the third-level and fourth-level correction surfaces of the drum and the magnitude of the real-time imbalance of the fourth-level and third-level correction surfaces of the drum, balance the difference between the real-time imbalance of the third-level and fourth-level correction surfaces of the drum or the first-level and sixth-level correction surfaces of the drum and its corresponding initial imbalance to less than or equal to 50 g•mm.

[0051] This step first calculates the phase difference of the initial imbalance of the third and fourth level correction surfaces of the drum, and then performs balance adjustment based on the phase difference and the real-time imbalance of the third and fourth level correction surfaces of the drum.

[0052] Specifically, when the phase difference between the real-time imbalance of the third-level and fourth-level correction surfaces of the drum is greater than 100° and the value of the real-time imbalance of the third-level correction surface is greater than the value of the real-time imbalance of the fourth-level correction surface, first balance the first-level correction surface of the drum to reduce the real-time imbalance of the third-level correction surface by 1 / 3, then balance the sixth-level correction surface of the drum to reduce the real-time imbalance of the fourth-level correction surface by 1 / 3, and finally balance the third-level and fourth-level correction surfaces of the drum until the difference between their real-time imbalance and their corresponding initial imbalance is less than 50 g•mm.

[0053] When the phase difference between the real-time imbalance of the third and fourth level correction surfaces of the drum is greater than 100° and the value of the real-time imbalance of the third level correction surface is less than the value of the real-time imbalance of the fourth level correction surface, first balance the sixth level correction surface of the drum to reduce the real-time imbalance of the fourth level correction surface by 1 / 3, then balance the first level correction surface of the drum to reduce the real-time imbalance of the third level correction surface by 1 / 3, and finally balance the third and fourth level correction surfaces of the drum until the difference between their real-time imbalance and their corresponding initial imbalance is less than 50 g•mm.

[0054] When the phase difference between the real-time unbalance of the third-level and fourth-level correction surfaces of the drum is less than or equal to 100° and the value of the real-time unbalance of the third-level correction surface is greater than the value of the real-time unbalance of the fourth-level correction surface, first balance the third-level correction surface of the drum so that its unbalance is equal in magnitude and opposite in direction to that of the fourth-level correction surface of the drum. Then balance the first-level and sixth-level correction surfaces of the drum until the difference between its real-time unbalance and its corresponding initial unbalance is less than 50 g•mm.

[0055] When the phase difference between the real-time unbalance of the third-level and fourth-level correction surfaces of the drum is less than or equal to 100° and the magnitude of the real-time unbalance of the third-level correction surface is less than the magnitude of the real-time unbalance of the fourth-level correction surface, first balance the fourth-level correction surface so that its unbalance is equal in magnitude and opposite in direction to that of the third-level correction surface. Then balance the first-level and sixth-level correction surfaces of the drum until the difference between its real-time unbalance and its corresponding initial unbalance is less than 50 g•mm.

[0056] Step S16: Remove the high-pressure rotor from the balancing machine and assemble the rotor disc and shaft onto the high-pressure rotor.

[0057] Step S17: Hoist the high-pressure rotor onto the dynamic balancing machine and balance the real-time unbalance values ​​of the rotor front end correction surface 81 and the rotor rear end correction surface 86 to less than or equal to 10 g•mm.

[0058] The above method achieves precise balancing by balancing the first, third, fourth, and sixth stage rotor correction surfaces of the high-pressure compressor drum in a step-by-step manner according to a logical sequence. After balancing, the unbalanced torque inside the rotor system is reduced. The reduced bending deformation of the flexible rotor under unbalanced excitation at high speed effectively suppresses vibration faults in a certain type of aero-engine and reduces engine maintenance costs.

[0059] This method achieves gradual balancing, eliminating unbalanced torques inside the rotor step by step, thereby eliminating or reducing unbalanced excitations generated at high speeds, eliminating or reducing rotor bending deformation, and thus reducing vibration amplitude and eliminating vibration faults.

[0060] Those skilled in the art will recognize that the embodiments described herein are intended to help the reader understand the principles of the invention, and should be understood that the scope of protection of the invention is not limited to such specific statements and embodiments. Those skilled in the art can make various other specific modifications and combinations based on the technical teachings disclosed in this invention without departing from the spirit of the invention, and these modifications and combinations are still within the scope of protection of this invention.

Claims

1. A method for progressive balancing of a high-pressure compressor rotor drum of an aero-engine, characterized in that, Includes the following steps: The front journal end of the high-pressure rotor is fixed with a fixed bracket, and the six-stage rotor is fixed on the pressure plate of the fixed bracket. A balancing device is installed on the high-pressure rotor; After hoisting the high-pressure rotor onto the dynamic balancing machine, the factory counterweights are installed on each calibration surface. Then, the initial imbalance of the third-level calibration surface, the fourth-level calibration surface, the first-level calibration surface, and the sixth-level calibration surface of the drum is measured. After removing the factory counterweights from each calibration surface in situ, measure the real-time imbalance of the third-level calibration surface, the fourth-level calibration surface, the first-level calibration surface, and the sixth-level calibration surface of the drum again. Based on the phase difference of the real-time imbalance of the third-level and fourth-level correction surfaces of the drum and the magnitude of the real-time imbalance of the fourth-level and third-level correction surfaces of the drum, the difference between the real-time imbalance of the third-level and fourth-level correction surfaces of the drum or the first-level and sixth-level correction surfaces of the drum and its corresponding initial imbalance is balanced to less than or equal to 50 g•mm. Remove the high-pressure rotor from the balancing machine and assemble the rotor disc and shaft onto the high-pressure rotor; The high-pressure rotor is hoisted onto the dynamic balancing machine, and the real-time imbalance values ​​of the rotor front end correction surface and the rotor rear end correction surface are balanced to less than or equal to 10 g•mm.

2. The method for progressive balancing of a high-pressure compressor rotor drum of an aero-engine according to claim 1, characterized in that, The balancing device assembled on the high-pressure rotor includes: Operate the fixed bracket to raise the front journal end of the high-pressure rotor, and assemble the process bearing at the front journal end; Install a balancing device on the process bearing and operate the fixed bracket to make the sixth-stage rotor end face upward; The heating balance device has a six-stage positioning plate, which fixes the six-stage positioning plate and the six-stage rotor end.

3. The method for progressive balancing of a high-pressure compressor rotor drum of an aero-engine according to claim 1, characterized in that, The step of balancing the difference between the real-time imbalance of the third-level and fourth-level correction surfaces of the drum and the corresponding initial imbalance of the fourth-level and third-level correction surfaces of the drum to less than or equal to 50 g·mm, based on the phase difference of the real-time imbalance of the third-level and fourth-level correction surfaces of the drum or the first-level and sixth-level correction surfaces of the drum, includes: Calculate the phase difference of the initial unbalance on the third and fourth level correction surfaces of the drum. When the phase difference between the real-time imbalance of the third-level and fourth-level correction surfaces of the drum is greater than 100° and the value of the real-time imbalance of the third-level correction surface is greater than the value of the real-time imbalance of the fourth-level correction surface, first balance the first-level correction surface of the drum to reduce the real-time imbalance of the third-level correction surface by 1 / 3, then balance the sixth-level correction surface of the drum to reduce the real-time imbalance of the fourth-level correction surface by 1 / 3, and finally balance the third-level and fourth-level correction surfaces of the drum until the difference between their real-time imbalance and their corresponding initial imbalance is less than 50 g•mm. When the phase difference between the real-time imbalance of the third and fourth level correction surfaces of the drum is greater than 100° and the value of the real-time imbalance of the third level correction surface is less than the value of the real-time imbalance of the fourth level correction surface, first balance the sixth level correction surface of the drum to reduce the real-time imbalance of the fourth level correction surface by 1 / 3, then balance the first level correction surface of the drum to reduce the real-time imbalance of the third level correction surface by 1 / 3, and finally balance the third and fourth level correction surfaces of the drum until the difference between their real-time imbalance and their corresponding initial imbalance is less than 50 g•mm.

4. The method for progressive balancing of a high-pressure compressor rotor drum of an aero-engine according to claim 3, characterized in that, The calculation of the phase difference of the initial unbalance of the third-level and fourth-level correction surfaces of the drum also includes: When the phase difference between the real-time unbalance of the third-level and fourth-level correction surfaces of the drum is less than or equal to 100° and the value of the real-time unbalance of the third-level correction surface is greater than the value of the real-time unbalance of the fourth-level correction surface, first balance the third-level correction surface of the drum so that its unbalance is equal in magnitude and opposite in direction to that of the fourth-level correction surface of the drum. Then balance the first-level and sixth-level correction surfaces of the drum until the difference between its real-time unbalance and its corresponding initial unbalance is less than 50 g•mm. When the phase difference between the real-time unbalance of the third-level and fourth-level correction surfaces of the drum is less than or equal to 100° and the magnitude of the real-time unbalance of the third-level correction surface is less than the magnitude of the real-time unbalance of the fourth-level correction surface, first balance the fourth-level correction surface so that its unbalance is equal in magnitude and opposite in direction to that of the third-level correction surface. Then balance the first-level and sixth-level correction surfaces of the drum until the difference between its real-time unbalance and its corresponding initial unbalance is less than 50 g•mm.

5. The method for progressive balancing of a high-pressure compressor rotor drum of an aero-engine according to claim 1, characterized in that, The balancing device includes a balancing device body, a six-stage positioning plate disposed at one end of the balancing device body, and a flange positioning plate disposed at the other end of the balancing device body.

6. The method for progressive balancing of a high-pressure compressor rotor drum of an aero-engine according to claim 1, characterized in that, The fixed support includes a support frame (11), a high-pressure rotor fixture rotatably mounted on the support frame (11), and a control component (12) for controlling the rotation of the high-pressure rotor fixture. The high-pressure rotor frame includes at least two connecting rods (13), a support rod (14) fixed to one end of the connecting rod (13) and placed on the same plane for supporting the front journal end, a fixing plate (16) fixed to the other end of the connecting rod (13), a pressure plate (15) placed between the support rod (14) and the fixing plate (16), and an adjusting screw (17) connected between the pressure plate (15) and the fixing plate (16) for adjusting the distance between the support rod (14) and the pressure plate (15).

7. The method for progressive balancing of a high-pressure compressor rotor drum of an aero-engine according to claim 6, characterized in that, The support frame (11) is provided with rollers (18) at its bottom.

8. The method for progressive balancing of a high-pressure compressor rotor drum of an aero-engine according to claim 6, characterized in that, There are three connecting rods (13), which are arranged in parallel to each other. Two of the connecting rods (13) are rotatably mounted on the support frame (11).

9. The method for progressive balancing of a high-pressure compressor rotor drum of an aero-engine according to claim 6, characterized in that, The pressure plate (15) is semi-circular.

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