Multi-correction-surface progressive balancing method for rotor drum of high-pressure compressor of aero-engine

Abstract

The invention discloses a multi-correction-face progressive balancing method for a rotor drum of a high-pressure compressor of an aero-engine. The multi-correction-face progressive balancing method comprises the following steps that after a high-pressure rotor is hoisted to a dynamic balancing machine, a balance weight is assembled, and then the initial unbalance amount is measured; the real-time unbalance amount is measured again after the balance weight is taken down; according to the real-time unbalance amount phase difference of the drum three-stage correction surface and the drum four-stage correction surface and the real-time unbalance amount values of the drum four-stage correction surface and the drum three-stage correction surface, the drum three-stage correction surface and the drum four-stage correction surface are corrected; balancing the difference value between the real-time unbalance amount of the drum third-stage correction surface and the drum fourth-stage correction surface or between the real-time unbalance amount of the drum first-stage correction surface and the drum sixth-stage correction surface and the corresponding initial unbalance amount to be smaller than or equal to 50g mm; detaching the high-pressure rotor, and assembling a rotor disc and a shaft; and balancing the real-time unbalance values of the rotor front end correction surface and the rotor rear end correction surface to be less than or equal to 10g mm. According to the method, the unbalanced torque in the rotor is eliminated step by step, and the deflection deformation of the flexible rotor caused by unbalanced excitation at a high rotating speed is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of rotor drum correction surface balancing, and in particular relates to a multi-correction surface progressive balancing method for a rotor drum of an aero-engine high-pressure compressor. Background Art

[0002] Aircraft engine vibration failure refers to abnormal vibration phenomena that occur during the operation of aircraft engines. These failures not only affect the normal operation of the engine, but may also have a serious impact on its life and flight safety. The causes of vibration failures are varied, mainly including rotor imbalance, rotor-stator friction, misalignment, thermal bending, blade vibration, etc.

[0003] The existing rotor balancing adopts the "step-by-step balancing method for reinforced disc compressor rotor" with application number CN202311036176.8, which includes the following steps: S101: Perform static balancing adjustment on the rotating shaft to within an allowable range, and mark the mass focus of the rotating shaft; S102: installing the intermediate-stage impeller on the rotating shaft based on the mass point obtained in S101; S103: Perform static balance adjustment on the intermediate rotor obtained in S102, adjust it to an allowable range and mark the quality focus; S104: installing two impellers of the intermediate-stage impeller on both sides of the shaft axially based on the mass point obtained in S103; S105: Perform dynamic balancing adjustment on the intermediate rotor finally obtained, adjust it to within the allowable range and mark the quality points; S106: installing two impellers of the intermediate-stage impeller on both sides of the shaft axially based on the final mass point obtained; S107: Repeat S105-S106 until all impellers are installed, and adjust the dynamic balance of the compressor rotor to within an allowable range.

[0004] Since the rotor body of a certain type of aircraft engine high-pressure compressor is an elastic and flexible rotor and has the property of crossing multiple critical speeds during operation, the balanced rotor installed by the above method has poor balance. Summary of the invention

[0005] In order to solve the problem of poor rotor balance of elastic flexible rotor installation balance in the existing method, the present invention proposes a multi-correction surface progressive balancing method for a high-pressure compressor rotor drum of an aero-engine.

[0006] The objective of the present invention is achieved through the following technical solutions: The present invention discloses a multi-correction surface progressive balancing method for a rotor drum of a high-pressure compressor of an aeroengine, which comprises the following steps: A fixed bracket is used to fix the front journal end of the high-pressure rotor, and the six-stage rotor is fixed on the pressure plate of the fixed bracket; Install a balancing device on the high-pressure rotor; After hoisting the high-pressure rotor onto the dynamic balancing machine, install the factory weights on each correction surface and measure the initial unbalance of the third-level correction surface, fourth-level correction surface, first-level correction surface and sixth-level correction surface of the drum; After removing the factory weights from the correction surfaces, measure the real-time imbalance of the third-level correction surface, the fourth-level correction surface, the first-level correction surface, and the sixth-level correction surface of the drum again; According to the phase difference of the real-time unbalance amount of the third-level correction surface and the fourth-level correction surface of the drum and the value of the real-time unbalance amount of the fourth-level correction surface and the third-level correction surface of the drum, the difference between the real-time unbalance amount of the third-level correction surface and the fourth-level correction surface of the drum or the first-level correction surface and the sixth-level correction surface of the drum and the corresponding initial unbalance amount is balanced to be less than or equal to 50g•mm; Remove the high-pressure rotor from the balancing machine and assemble the rotor disc and shaft on the high-pressure rotor; Hoist the high-pressure rotor onto the dynamic balancing machine and balance the real-time unbalance values ​​of the rotor front end correction surface and the rotor rear end correction surface to less than or equal to 10g•mm.

[0007] The beneficial effects of the present invention are: The present invention eliminates the unbalanced torque inside the rotor step by step through a multi-correction surface progressive balancing method, which can significantly reduce the degree of bending deformation of the flexible rotor caused by unbalanced excitation at high speeds, thereby achieving the effect of reducing the vibration amplitude and eliminating vibration faults. Ordinary low-speed dynamic balancing equipment can be used to achieve the effect of using high-speed dynamic balancing equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0009] Figure 1 is a schematic diagram of the structure of the fixed bracket; Figure 2 It is a structural schematic diagram of the balancing device; Figure 3 It is a schematic diagram of the structure of the high-pressure rotor. DETAILED DESCRIPTION

[0010] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0011] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0012] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features of the embodiments may be combined with each other.

[0013] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0014] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the product of the invention is usually placed when in use, or the positions or positional relationships commonly understood by those skilled in the art, which are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0015] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0016] The present invention discloses a multi-correction surface progressive balancing method for a high-pressure compressor rotor drum of an aircraft engine, the method comprising steps S11 to S17. It should be noted that the step identifiers in this scheme are only for the convenience of explaining the method, and do not constitute a sequence limitation. The sequence of each step is based on its language description and the sequence of each signal.

[0017] Step S11: Use a fixed bracket to fix the front journal end of the high-pressure rotor, and fix the six-stage rotor on the pressure plate of the fixed bracket.

[0018] The overall schematic diagram of the high pressure rotor is as follows 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 therebetween are assembled on the high-pressure rotor, that is, only the first-stage rotor, the second-stage rotor, the third-stage rotor, the fourth-stage rotor, the fifth-stage rotor and the sixth-stage rotor are assembled. One end of the first-stage rotor is the front journal end.

[0019] Specifically, the structure of the fixing bracket is as follows: Figure 3 As shown, it includes a support frame 11, a high-pressure rotor frame rotatably arranged on the support frame 11, and a control component 12 for controlling the rotation of the high-pressure rotor frame; the high-pressure rotor frame includes at least two connecting rods 13, a support rod 14 fixed at one end of the connecting rod 13 and placed on the same plane for supporting the front journal end, a fixing plate 16 fixed at the other end of the connecting rod 13, a pressing plate 15 placed between the support rod 14 and the fixing plate 16, and an adjusting screw 17 connected between the pressing plate 15 and the fixing plate 16 for adjusting the distance between the support rod 14 and the pressing plate 15.

[0020] In order to facilitate movement and operation, a roller 18 is provided at the bottom of the support frame 11.

[0021] In order to enhance the structural stability and simplify the structure, there are three connecting rods 13 which are arranged parallel to each other, wherein two connecting rods 13 are rotatably arranged on the support frame 11 .

[0022] For ease of operation, Figure 1 As shown, the pressing plate 15 is in a semicircular shape.

[0023] It should be noted that Figure 1 Component 2 in the figure is a sample for installation example and is not a high-pressure rotor.

[0024] The fixing bracket has a simple structure. When fixing, the high-pressure rotor is placed into the fixing bracket from one end of the opening of the pressure plate 15, and its front journal end is placed on the support rod 14. Then the adjusting screw 17 is rotated to press the pressure plate 15 onto the end face of the six-stage rotor to fix the high-pressure rotor.

[0025] Step S12: assembling a balancing device on the high-pressure rotor.

[0026] Specifically, this step first operates the fixed bracket, operates the control component 12 to rotate the high-pressure rotor fixed bracket so that the front shaft neck end of the high-pressure rotor faces upward, and assembles the process bearing on the front shaft neck end; then assembles the balancing device on the process bearing, operates the fixed bracket, that is, rotates the high-pressure rotor fixed bracket so that the six-stage rotor end faces upward; finally, heats the six-stage positioning plate of the balancing device, and fixes the six-stage positioning plate and the six-stage rotor.

[0027] 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 arranged at one end of the balancing device body 6, and a flange positioning plate 5 arranged at the other end of the balancing device body 6.

[0028] The balancing device is connected and fixed to the outer steel sleeve of the process bearing through the flange positioning plate 5.

[0029] Step S13, after hoisting the high-pressure rotor onto the dynamic balancing machine, install the factory weights used in the last maintenance on each correction surface, and then measure the initial unbalance amounts of the drum's third-level correction surface 83, the drum's fourth-level correction surface 84, the drum's first-level correction surface 82, and the drum's sixth-level correction surface 85.

[0030] Step S14, after removing each correction surface in situ and installing the factory counterweight, measure the initial unbalance of the third-level correction surface, the fourth-level correction surface, the first-level correction surface and the sixth-level correction surface of the drum again.

[0031] In this step, the factory weight is the factory weight at the time of the last maintenance and is the standard weight.

[0032] Step S15, based on the phase difference of the real-time imbalance of the third-level correction surface and the fourth-level correction surface of the drum and the value of the real-time imbalance of the fourth-level correction surface and the third-level correction surface of the drum, balance the difference between the real-time imbalance of the third-level correction surface and the fourth-level correction surface of the drum or the first-level correction surface and the sixth-level correction surface of the drum and their corresponding initial imbalance to be less than or equal to 50g•mm.

[0033] This step first calculates the phase difference of the initial imbalance of the drum's third-level correction surface and the drum's fourth-level correction surface, and then performs balancing adjustment based on the phase difference and the real-time imbalance of the drum's third-level correction surface and the drum's fourth-level correction surface.

[0034] Specifically, when the phase difference of the real-time unbalance amount of the third-level correction surface of the drum and the fourth-level correction surface of the drum is greater than 100° and the value of the real-time unbalance amount of the third-level correction surface of the drum is greater than the value of the real-time unbalance amount of the fourth-level correction surface of the drum, the first-level correction surface of the drum is balanced first to reduce the real-time unbalance amount of the third-level correction surface of the drum by 1 / 3, and then the sixth-level correction surface of the drum is balanced to reduce the real-time unbalance amount of the fourth-level correction surface of the drum by 1 / 3, and finally the third-level correction surface of the drum and the fourth-level correction surface of the drum are balanced respectively until the difference between their real-time unbalance amount and their corresponding initial unbalance amount is less than 50g•mm; When the phase difference of the real-time unbalance of the third-level correction surface and the fourth-level correction surface of the drum is greater than 100° and the value of the real-time unbalance of the third-level correction surface of the drum is smaller than the value of the real-time unbalance of the fourth-level correction surface of the drum, first balance the sixth-level correction surface of the drum to reduce the real-time unbalance of the fourth-level correction surface of the drum by 1 / 3, then balance the first-level correction surface of the drum to reduce the real-time unbalance of the third-level correction surface of the drum by 1 / 3, and finally balance the third-level correction surface and the fourth-level correction surface of the drum until the difference between their real-time unbalance and their corresponding initial unbalance is less than 50g•mm.

[0035] When the phase difference of the real-time unbalance amount of the third-level correction surface of the drum and the fourth-level correction surface of the drum is less than or equal to 100° and the value of the real-time unbalance amount of the third-level correction surface of the drum is greater than the value of the real-time unbalance amount of the fourth-level correction surface of the drum, first balance the third-level correction surface of the drum so that its unbalance amount is equal to the unbalance amount of the fourth-level correction surface of the drum and opposite in direction, and then balance the first-level correction surface of the drum and the sixth-level correction surface of the drum respectively until the difference between their real-time unbalance amount and their corresponding initial unbalance amount is less than 50g•mm; When the phase difference of the real-time unbalance of the third-level correction surface and the fourth-level correction surface of the drum is less than or equal to 100° and the value of the real-time unbalance of the third-level correction surface of the drum is smaller than the value of the real-time unbalance of the fourth-level correction surface of the drum, first balance the fourth-level correction surface of the drum so that its unbalance is equal to and opposite to the unbalance of the third-level correction surface of the drum, and then balance the first-level correction surface and the sixth-level correction surface of the drum until the difference between their real-time unbalance and their corresponding initial unbalance is less than 50g•mm.

[0036] Step S16: remove the high-pressure rotor from the balancing machine, and assemble the rotor disk and the shaft on the high-pressure rotor.

[0037] Step S17, hoisting the high-pressure rotor onto the dynamic balancing machine, balancing the real-time unbalance values ​​of the rotor front end correction surface 81 and the rotor rear end correction surface 86 to be less than or equal to 10 g·mm.

[0038] The above method achieves precise balancing by balancing the first-stage, third-stage, fourth-stage and sixth-stage rotor correction surfaces of the high-pressure compressor drum and executing it step by step in a logical order. After balancing, the unbalanced torque inside the rotor system is reduced, and the bending deformation of the flexible rotor caused by unbalanced excitation at high speed is reduced, which effectively suppresses the vibration failure of a certain type of aircraft engine and reduces the engine maintenance cost.

[0039] This method is used to achieve progressive balancing and eliminate the unbalanced torque inside the rotor step by step, thereby eliminating or reducing the unbalanced excitation generated at high speed and eliminating or reducing the rotor bending deformation, so as to achieve the effect of reducing the vibration amplitude and eliminating vibration faults.

[0040] Those skilled in the art will appreciate that the embodiments described herein are intended to help readers understand the principles of the present invention, and should be understood that the protection scope of the present invention is not limited to such specific statements and embodiments. Those skilled in the art can make various other specific variations and combinations that do not deviate from the essence of the present invention based on the technical revelations disclosed by the present invention, and these variations and combinations are still within the protection scope of the present invention.

Claims

1. A multi-correction surface progressive balancing method for a high-pressure compressor rotor drum of an aircraft engine, characterized in that: The following steps are involved: A fixed bracket is used to fix the front journal end of the high-pressure rotor, and the six-stage rotor is fixed on the pressure plate of the fixed bracket; Install a balancing device on the high-pressure rotor; After hoisting the high-pressure rotor onto the dynamic balancing machine, install the factory weights on each correction surface and measure the initial unbalance of the third-level correction surface, fourth-level correction surface, first-level correction surface and sixth-level correction surface of the drum; After removing the factory weights from the correction surfaces, measure the real-time imbalance of the third-level correction surface, the fourth-level correction surface, the first-level correction surface, and the sixth-level correction surface of the drum again; According to the phase difference of the real-time unbalance amount of the third-level correction surface and the fourth-level correction surface of the drum and the value of the real-time unbalance amount of the fourth-level correction surface and the third-level correction surface of the drum, the difference between the real-time unbalance amount of the third-level correction surface and the fourth-level correction surface of the drum or the first-level correction surface and the sixth-level correction surface of the drum and the corresponding initial unbalance amount is balanced to be less than or equal to 50g•mm; Remove the high-pressure rotor from the balancing machine and assemble the rotor disc and shaft on the high-pressure rotor; Hoist the high-pressure rotor onto the dynamic balancing machine and balance the real-time unbalance values ​​of the rotor front end correction surface and the rotor rear end correction surface to less than or equal to 10g•mm.

2. The method for progressive balancing of a multi-correction surface of a rotor drum of an aircraft engine high-pressure compressor according to claim 1, characterized in that: The balancing device is assembled on the high-pressure rotor, comprising: Operate the fixed bracket to make the front journal end of the high-pressure rotor face upward, and assemble the process bearing on the front journal end; Assemble the balancing device on the process bearing and operate the fixing bracket so that the end of the sixth-stage rotor faces upward; The six-stage positioning plate of the heating balancing device fixes the six-stage positioning plate and the six-stage rotor end.

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

4. The method for progressive balancing of a multi-correction surface of a rotor drum of an aircraft engine high-pressure compressor according to claim 3, characterized in that: After calculating the phase difference of the initial unbalance amount of the third-level correction surface of the drum and the fourth-level correction surface of the drum, the following steps are further included: When the phase difference of the real-time unbalance amount of the third-level correction surface of the drum and the fourth-level correction surface of the drum is less than or equal to 100° and the value of the real-time unbalance amount of the third-level correction surface of the drum is greater than the value of the real-time unbalance amount of the fourth-level correction surface of the drum, first balance the third-level correction surface of the drum so that its unbalance amount is equal to the unbalance amount of the fourth-level correction surface of the drum and opposite in direction, and then balance the first-level correction surface of the drum and the sixth-level correction surface of the drum respectively until the difference between their real-time unbalance amount and their corresponding initial unbalance amount is less than 50g•mm; When the phase difference of the real-time unbalance of the third-level correction surface and the fourth-level correction surface of the drum is less than or equal to 100° and the value of the real-time unbalance of the third-level correction surface of the drum is smaller than the value of the real-time unbalance of the fourth-level correction surface of the drum, first balance the fourth-level correction surface of the drum so that its unbalance is equal to and opposite to the unbalance of the third-level correction surface of the drum, and then balance the first-level correction surface and the sixth-level correction surface of the drum until the difference between their real-time unbalance and their corresponding initial unbalance is less than 50g•mm.

5. The method for progressive balancing of a multi-correction surface of a rotor drum of an aircraft engine high-pressure compressor according to claim 1, characterized in that: The balancing device comprises a balancing device body, a six-level positioning plate arranged at one end of the balancing device body, and a flange positioning plate arranged at the other end of the balancing device body.

6. The method for progressive balancing of a multi-correction surface of a rotor drum of an aircraft engine high-pressure compressor according to claim 1, characterized in that: The fixed support comprises a support frame (11), a high-pressure rotor fixed frame rotatably arranged on the support frame (11), and a control component (12) for controlling the rotation of the high-pressure rotor fixed frame; The high-pressure rotor frame comprises 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 multi-correction surface of a rotor drum of an aircraft engine high-pressure compressor according to claim 6, characterized in that: A roller (18) is provided at the bottom of the support frame (11).

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

9. The method for progressive balancing of a multi-correction surface of a rotor drum of an aircraft engine high-pressure compressor according to claim 6, characterized in that: The pressing plate (15) is in a semicircular arc shape.

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