A dynamic balancing method for reducing the rotational inertia load of a high-pressure rotor

Abstract

The application belongs to the technical field of aero-engines, and particularly relates to a dynamic balancing method for reducing the rotating inertia load of a high-pressure rotor. The initial unbalance amount phase difference of front and rear modification surfaces of each component of the high-pressure rotor is measured respectively, and the initial static unbalance amount grade of the component is controlled according to the initial unbalance amount phase difference of the component. The coaxiality of the front and rear ends of each component is measured respectively, and the coaxiality is controlled to be not greater than φ0.02mm. Each component is assembled into the high-pressure rotor, the coaxiality of the component connection of the high-pressure rotor is measured, and the coaxiality is controlled to be not greater than φ0.015mm. The initial unbalance amount phase difference of the front and rear modification surfaces of the high-pressure rotor is measured, and the initial static unbalance amount grade of the high-pressure rotor is controlled according to the initial unbalance amount phase difference. The residual static unbalance amount grade of the high-pressure rotor and the residual unbalance amount grade of the front and rear modification surfaces are controlled according to the initial unbalance amount phase difference, which can effectively reduce the inclination degree of the main inertia axis of the high-pressure rotor, and further reduce the rotating inertia excitation load under high speed.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engines, and particularly relates to a dynamic balancing method for reducing the rotational inertia load of a high-pressure rotor. BACKGROUND

[0002] Rotational inertia excitation is one of the main excitation sources of rotor vibration of an aero-engine, and the main source of rotational inertia excitation load is the imbalance of the rotor. Therefore, the balancing method and balancing quality have a great influence on the vibration of the whole machine. The high-pressure rotor of an aero-engine is composed of a compressor rotor and a turbine rotor, and has a high working speed, generally working above the rigid body critical speed. In the actual working process of the rotor, the rotational inertia load is not only related to the centrifugal force caused by the mass center offset of the rotor, but also mainly affected by the inertia moment caused by the inclination of the main inertia axis of the rotor, especially after the rotor speed passes through the rigid body critical speed. The rotational inertia load excitation caused by the mass center offset of the rotor will decrease, but the rotational inertia moment excitation load caused by the inclination of the main inertia axis of the rotor will continue to increase, which will have an adverse effect on the rotor vibration.

[0003] The high-pressure rotor of an aero-engine usually adopts a step-by-step low-speed balancing method. On the basis of balancing the zero components, the dynamic balancing of the compressor rotor and the turbine rotor is completed respectively, and then the combined balancing of the rotor is carried out after the compressor and the turbine rotor are assembled together. The speed of the high-pressure rotor is generally within 10000-20000 r / min, and the actual working speed of the rotor cannot be used for balancing during assembly and balancing. Generally, the balancing is carried out at a speed of 800-1200 r / min. At this balancing speed, only the rotational inertia force caused by the mass center offset of the rotor can be measured and corrected, and the rotational inertia moment caused by the inclination of the main inertia axis of the rotor cannot be measured and corrected.

[0004] Therefore, under the condition that the working speed cannot be used for balancing the high-pressure rotor, the uniformity of the mass and the mass correction distribution of each component of the rotor along the axial direction needs to be fully considered during the step-by-step balancing of the high-pressure rotor. According to the imbalance size and phase of the rotor components during the balancing of the rotor assembly and the combination, a rotor balancing quality control method is formulated.

[0005] The disadvantages of the previous high-pressure rotor balancing method are as follows:

[0006] The assembly and balancing of the high-pressure rotor are to assemble the compressor rotor and the turbine rotor respectively, measure the initial imbalance of the two rotor assemblies, and then assemble the compressor and the turbine rotor together for balancing correction. Due to the limitation of low-speed dynamic balancing, the previous method may cause the following problems:

[0007] 1. The uncontrolled compressor rotor, turbine rotor, and high-pressure rotor coaxiality after assembly, the rotor assembly after the combined balance only to measure and correct the rotor mass center offset, the initial inclination of the inertia main shaft of the entire high-pressure rotor is not measured and controlled.

[0008] 2. When the initial imbalance of the compressor and turbine rotors is controlled according to the phase of the initial imbalance of the compressor and turbine rotors, the compressor and turbine rotors themselves may have a large inertia main shaft inclination.

[0009] 3. When the compressor and turbine rotors are assembled together for high-pressure rotor combined balancing, only the remaining imbalance of the rotor is corrected to the qualified level, and the phase change of the front and rear imbalance of the rotor after correction is not concerned, which may increase the inertia main shaft of the rotor and further affect the vibration response of the rotor at high speed. SUMMARY

[0010] To solve the above problems, the application provides a dynamic balancing method for reducing the rotational inertia load of a high-pressure rotor, comprising:

[0011] Step 1: Measure the initial imbalance phase difference of the front and rear correction surfaces of each component of the high-pressure rotor respectively, when the initial imbalance phase difference of the component is less than or equal to 60°, the initial static imbalance of the component is controlled to be not greater than G6.3 level; when the initial imbalance phase difference of the component is greater than 60°, the initial static imbalance of the component is controlled to be not greater than G2.5 level, and the initial imbalance of the front and rear correction surfaces is not greater than G6.3 level; the components include a compressor rotor and a turbine rotor;

[0012] Step 2: Measure the coaxiality of the front and rear ends of each component respectively, and control the coaxiality to be not greater than φ0.02mm;

[0013] Step 3: Assemble each component into a high-pressure rotor, measure the coaxiality of the component connection of the high-pressure rotor, and control the coaxiality to be not greater than φ0.015mm;

[0014] Step 4: Measure the initial imbalance phase difference of the front and rear correction surfaces of the high-pressure rotor, when the initial imbalance phase difference of the high-pressure rotor is less than or equal to 60°, the initial static imbalance of the high-pressure rotor is controlled to be not greater than G6.3 level; when the initial imbalance phase difference of the high-pressure rotor is greater than 60°, the initial static imbalance of the high-pressure rotor is controlled to be not greater than G2.5 level, and the initial imbalance of the front and rear correction surfaces is not greater than G6.3 level;

[0015] Step 5: When the phase difference of the initial unbalance of the front and rear modification surfaces of the high-pressure rotor is less than or equal to 60°, install a balance correction block on the front and rear modification surfaces of the high-pressure rotor, and control the residual static unbalance of the high-pressure rotor to be not greater than G1.0 grade; when the phase difference of the initial unbalance of the front and rear modification surfaces of the high-pressure rotor is greater than 60°, control the residual static unbalance of the high-pressure rotor to be not greater than G1.0 grade, and control the residual unbalance of the front and rear modification surfaces of the high-pressure rotor to be not greater than G2.5 grade.

[0016] Preferably, before step 1, each part of the high-pressure rotor is separately subjected to low-speed dynamic balancing, so that the residual unbalance of each part meets G1.0 grade.

[0017] Preferably, after the balance correction block is installed on the front and rear modification surfaces of the high-pressure rotor, the difference between the phase of the residual unbalance of the modification surface and the phase of the initial unbalance of the modification surface is within the range of 0°-60°.

[0018] Preferably, the balance correction block installed on the same modification surface is not more than two.

[0019] Preferably, the installation phase of the balance correction block is outside the range of 160°-180°.

[0020] Preferably, the initial static unbalance of the control assembly is controlled in the following manner: re-machining or re-assembly of the assembly.

[0021] The advantages of the present application include: through low-speed dynamic balancing, the initial unbalance and phase of each component of the high-pressure rotor are controlled step by step, and through the balance correction method of controlling the inclination of the inertia main shaft of the rotor component, the inclination of the main inertia shaft of the high-pressure rotor can be effectively reduced, and thus the rotational inertia excitation load of the high-pressure rotor can be reduced. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 is a flow chart of a dynamic balancing method for reducing the rotational inertia load of a high-pressure rotor according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0023] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0024] As shown in Figure 1 , the present application provides a dynamic balancing method for reducing the rotational inertia load of a high-pressure rotor, comprising:

[0025] Step 1: Low-speed dynamic balancing is respectively performed on each part of the high-pressure rotor, so that the residual unbalance of each part meets the G1.0 level. The initial unbalance phase difference of each component of the high-pressure rotor is measured, and when the initial unbalance phase difference of the component is less than or equal to 60°, it indicates that the inertia load generated by the mass center deviation of the component dominates, and the initial static unbalance of the component is controlled to be not greater than the G6.3 level; when the initial unbalance phase difference of the component is greater than 60°, it indicates that both the rotational inertia force and the inertia moment generated by the mass center deviation and the inclination of the inertia main shaft of the component will have a great influence on the vibration of the component, and the initial static unbalance of the component is controlled to be not greater than the G2.5 level, and the initial unbalance of the front and rear correction surfaces is not greater than the G6.3 level; the components include the compressor rotor and the turbine rotor; wherein, the G1.0 level, the G6.3 level, etc. are rotor dynamic balancing precision levels defined in ISO 1940;

[0026] Step 2: The coaxialities of the front and rear ends of each component are respectively measured, and the coaxiality is controlled to be not greater than φ0.02mm; specifically including: the coaxiality of the front and rear ends of the compressor rotor and the turbine rotor is measured, and the joint or end tooth at the connection between the compressor rotor or the turbine rotor and the fulcrum bearing is taken as the reference, and the coaxiality at the fulcrum bearing is measured, and the coaxiality is required to be not greater than φ0.02mm.

[0027] Step 3: Assembling the components into the high-pressure rotor, taking the connection between the front and rear ends of the high-pressure rotor and the fulcrum bearing as the reference, measuring the coaxiality of the component connection of the high-pressure rotor, and controlling the coaxiality to be not greater than φ0.015mm; if the coaxiality does not meet the requirements, the connection angle phase of the compressor rotor and the turbine rotor is adjusted to make the coaxiality meet the requirements.

[0028] Step 4: The initial unbalance phase difference of the front and rear correction surfaces of the high-pressure rotor is measured, and when the initial unbalance phase difference of the high-pressure rotor is less than or equal to 60°, it indicates that the inertia load generated by the mass center deviation of the high-pressure rotor dominates, and the initial static unbalance of the high-pressure rotor is controlled to be not greater than the G6.3 level; when the initial unbalance phase difference of the high-pressure rotor is greater than 60°, it indicates that both the rotational inertia force and the inertia moment generated by the mass center deviation and the inclination of the inertia main shaft of the high-pressure rotor will have a great influence on the vibration of the high-pressure rotor, and the initial static unbalance of the high-pressure rotor is controlled to be not greater than the G2.5 level, and the initial unbalance of the front and rear correction surfaces is not greater than the G6.3 level;

[0029] Step 5: When the phase difference of the initial unbalance of the front and rear modification surfaces of the high-pressure rotor is less than or equal to 60°, install a balance modification block on the front and rear modification surfaces of the high-pressure rotor to control the residual static unbalance of the high-pressure rotor to be not greater than G1.0 grade; when the phase difference of the initial unbalance of the front and rear modification surfaces of the high-pressure rotor is greater than 60°, control the residual static unbalance of the high-pressure rotor to be not greater than G1.0 grade, and control the residual unbalance of the front and rear modification surfaces of the high-pressure rotor to be not greater than G2.5 grade. Wherein, it is strictly avoided to install multiple or large mass modification blocks on the front modification surface of the high-pressure rotor to modify the unbalance of the rear modification surface, and vice versa.

[0030] In some optional embodiments, after installing the balance modification block on the front and rear modification surfaces of the high-pressure rotor, the difference between the phase of the residual unbalance of the modification surface and the phase of the initial unbalance of the modification surface is within the range of 0°-60°.

[0031] In some optional embodiments, the balance modification block assembled on the same modification surface is not more than two.

[0032] In some optional embodiments, the installation phase of the balance modification block is outside the range of 160°-180°.

[0033] In some optional embodiments, the initial static unbalance of the control assembly is controlled in the following manner: re-machining or re-assembly of the assembly.

[0034] The advantages of the present application include: by low-speed dynamic balancing, step-by-step control of the initial unbalance and phase of each component of the high-pressure rotor, and by using the balance modification method of controlling the inclination of the inertia main shaft of the rotor component, the inclination of the main inertia shaft of the high-pressure rotor can be effectively reduced, and thus the rotational inertia excitation load at high speed can be reduced.

[0035] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any changes or replacements easily thought of by those skilled in the art within the technical range disclosed in the present application should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A dynamic balancing method for reducing the rotational inertial load of a high-voltage rotor, characterized in that, include: Step 1: Measure the initial imbalance phase difference of each component of the high-pressure rotor on the front and rear correction surfaces. When the initial imbalance phase difference of the component is less than or equal to 60°, control the initial static imbalance of the component to be no greater than G6.3 level; when the initial imbalance phase difference of the component is greater than 60°, control the initial static imbalance of the component to be no greater than G2.5 level, and the initial imbalance of the front and rear correction surfaces to be no greater than G6.3 level; the components include the compressor rotor and the turbine rotor; Step 2: Measure the coaxiality of the front and rear ends of each component separately, and control the coaxiality to be no greater than φ0.02mm; Step 3: Assemble the components into a high-pressure rotor, measure the coaxiality of the component connections of the high-pressure rotor, and control the coaxiality to be no greater than φ0.015mm; Step 4: Measure the initial unbalance phase difference between the front and rear correction surfaces of the high-voltage rotor. When the initial unbalance phase difference of the high-voltage rotor is less than or equal to 60°, control the initial static unbalance of the high-voltage rotor to be no greater than G6.3 level; when the initial unbalance phase difference of the high-voltage rotor is greater than 60°, control the initial static unbalance of the high-voltage rotor to be no greater than G2.5 level, and the initial unbalance of the front and rear correction surfaces to be no greater than G6.3 level. Step 5: When the initial unbalance phase difference between the front and rear correction surfaces of the high-voltage rotor is less than or equal to 60°, install balance correction blocks on the front and rear correction surfaces of the high-voltage rotor to control the remaining static unbalance of the high-voltage rotor to be no greater than G1.0 level; when the initial unbalance phase difference between the front and rear correction surfaces of the high-voltage rotor is greater than 60°, install balance correction blocks on the front and rear correction surfaces of the high-voltage rotor to control the remaining static unbalance of the high-voltage rotor to be no greater than G1.0 level, and control the remaining unbalance of the front and rear correction surfaces of the high-voltage rotor to be no greater than G2.5 level.

2. The dynamic balancing method for reducing the rotational inertial load of a high-voltage rotor as described in claim 1, characterized in that, Before step 1, each component of the high-pressure rotor is dynamically balanced at low speed to ensure that the remaining imbalance of each component meets the G1.0 level.

3. The dynamic balancing method for reducing the rotational inertial load of a high-voltage rotor as described in claim 1, characterized in that, After the balance correction blocks are installed on the front and rear correction surfaces of the high-pressure rotor, the difference between the phase of the remaining unbalance on the correction surface and the phase of the initial unbalance on the correction surface is within the range of 0° to 60°.

4. The dynamic balancing method for reducing the rotational inertial load of a high-voltage rotor as described in claim 1, characterized in that, No more than two balance correction blocks shall be assembled on the same correction surface.

5. The dynamic balancing method for reducing the rotational inertial load of a high-voltage rotor as described in claim 4, characterized in that, The balance correction block is installed outside the 160°~180° phase.

6. The dynamic balancing method for reducing the rotational inertial load of a high-voltage rotor as described in claim 1, characterized in that, The initial static imbalance of the components can be controlled by reprocessing or reassembling the components.

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