Equivalent flexible balance model and balance method suitable for aero-engine maintenance
Through the equivalent flexible balance model and the matching algorithm, the counterweight position adjustment and determination during the rotor of the aircraft engine is realized, and the problem of excessive unbalanced torque at high speed is solved, which improves maintenance quality and reduces vibration response.
Patent Information
- Application Number
- CN202411881639.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-19
- Publication Date
- 2025-03-14
AI Technical Summary
In the process of dynamic balance of the rotor of the aircraft engine, the weight adjustment is only performed on the equivalent plane, which cannot effectively solve the problem of excessive unbalanced torque at high speeds.
It provides an equivalent flexible balance model, including product visualization module, rotor data extraction and visualization module, balance calculation and construction guidance module, and visualization module, and realizes visualization and automatic calculation of balance parameters through statistical rectangular charts, adjusts the rotor weight of the multi-stage compressor to reduce the initial imbalance measurement.
It effectively reduces human errors, reduces balanced rework, improves aircraft engine maintenance quality, reduces vibration response during test runs, and solves the problem of not being able to reduce rotor imbalance under low-speed balance.
Smart Images
Figure CN119618465A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of aircraft engine maintenance, and in particular to an equivalent flexible balance model and a balance method suitable for aircraft engine maintenance. Background Art
[0002] Rotor dynamic balancing is of great significance in aircraft engine maintenance. Due to the high-speed rotation characteristics of aircraft engine rotors, their unbalanced state will have a serious impact on the stable operation and performance of the engine. Rotor imbalance will cause engine vibration, which may cause irreversible mechanical damage and reduce the reliability and service life of the engine.
[0003] In aircraft engine maintenance, dynamic balancing detection and adjustment of the rotor is a key step to ensure the normal operation of the engine. Through dynamic balancing technology, the imbalance of the rotor can be accurately measured, and the mass distribution of the rotor can be changed by adding or reducing counterweights. In the existing rotor dynamic balancing process, since the equivalent planes of the balancing machine only exist at both ends of the compressor rotor, the counterweight is only added or reduced on the equivalent plane during the balancing process. Under this balancing method, since the imbalance is only eliminated on the balancing surface, the problem of excessive unbalanced torque at high speed cannot be solved well.
[0004] The compressor rotor of a certain type of aircraft engine is a drum-disc structure with multi-stage disks and blades. During the balancing process, only the equivalent plane is balanced, which can only solve the imbalance problem at low speed. The even imbalance at high speed cannot be solved by eliminating the equivalent balance surface. Summary of the invention
[0005] In view of the above problems, the present invention provides an equivalent flexible balance model and a balance method suitable for aircraft engine maintenance.
[0006] The adopted technical solution is an equivalent flexible balance model suitable for aircraft engine maintenance, including a product visualization module, a rotor data extraction and visualization module, and a balance calculation and construction guidance module; The product visualization module is used to collect and visualize the positions of the counterweights of each stage, the size and angle of the unbalance of the equivalent plane, and the position of the circular runout of the compressor rotor; The rotor data extraction and visualization module is used to capture the balance characteristics and quality records in the work card system and complete the automatic input of data; The balance calculation and construction guidance module forms the balance weight position and data based on the input product data and equivalent flexible balance calculation.
[0007] The present application also provides an equivalent flexible balance method based on an equivalent flexible balance model applicable to aircraft engine maintenance, comprising the following steps: S1. Collect and organize the original data of aircraft engines and establish statistical rectangular charts; S2. Adjust the weight based on the initial imbalance of the rotor according to the statistical rectangular diagram; S3. Adjust the dynamic balance of the rotor based on the equivalent plane.
[0008] Furthermore, in S1, based on the vibration characteristics exhibited during the aircraft engine test, the assembly characteristics of the compressor rotor discs at each stage and the mass distribution characteristics of the compressor rotor, the parameters that affect the balancing result of the compressor rotor are selected.
[0009] Furthermore, in S1, the parameters include the counterweight position of each stage of the compressor rotor disk, the number of counterweights of each stage of the compressor rotor disk, the initial imbalance of the equivalent plane, the initial imbalance angle of the equivalent plane, the circular runout of the compressor rotor and the high point position of the compressor rotor runout.
[0010] Furthermore, in S2, the change of the initial unbalance is achieved by adjusting the counterweights on each stage of the compressor rotor disk, and the adjustment principle of the counterweights corresponds to the vibration characteristics exhibited during the aircraft engine test in S1.
[0011] Furthermore, in S3, the counterweight of the compressor rotor is equivalently increased or decreased according to the adjusted initial unbalance amount, so as to further reduce the unbalance amount of the compressor rotor.
[0012] The beneficial effects of the present invention are: 1. Provide an equivalent flexible balancing model and develop a corresponding algorithm to visualize the compressor rotor balancing parameters through statistical matrix diagrams, adjust and determine the counterweight position during dynamic balancing of the compressor rotor, visualize product data, and automatically calculate the balancing position, which can effectively reduce human errors, reduce balancing rework, improve the quality of aircraft engine maintenance, and reduce the vibration response during aircraft engine test runs; 2. By changing the multi-stage compressor rotor counterweight method, the initial imbalance of the compressor rotor can be reduced, thereby solving the problem that the rotor pair imbalance cannot be reduced under low-speed balancing. At the same time, an equivalent flexible balancing model is designed based on the method to visualize and solidify the balancing process. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 It is the operation interface of the equivalent flexible balance model; Figure 2 It is the equivalent plane module of the compressor rotor; Figure 3 It is the data extraction and data calculation module; Figure 4 This is the result of equivalent flexible balance calculation. DETAILED DESCRIPTION
[0014] The following describes the implementation of the present invention through specific examples. Those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific implementations, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.
[0015] It should be noted that the illustrations provided in the following embodiments are only used to schematically illustrate the basic concept of the present invention, and thus the drawings only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.
[0016] In this embodiment, an equivalent flexible balance model suitable for aircraft engine maintenance is provided, including a product visualization module, a rotor data extraction and visualization module, and a balance calculation and construction guidance module; The product visualization module is used to collect and visualize the positions of the counterweights of each stage, the size and angle of the unbalance of the equivalent plane, and the position of the circular runout of the compressor rotor; The rotor data extraction and visualization module is used to capture the balance characteristics and quality records in the work card system and complete the automatic input of data; The balance calculation and construction guidance module forms the balance weight position and data based on the input product data and equivalent flexible balance calculation.
[0017] The purpose of this design is to improve the efficiency of balancing after the model is applied. After the product data is entered, it can automatically calculate the unbalanced amount of the equivalent plane, visualize the calculation results, integrate multiple balancing data, and improve work efficiency. In the process of data extraction and data calculation, the product is automatically calculated, the balancing process replaces manual work, and human errors are reduced.
[0018] Meanwhile, in this embodiment, based on an equivalent flexible balance model applicable to aircraft engine maintenance, an equivalent flexible balance method is provided, comprising the following steps: S1. Collect and organize the original data of aircraft engines and establish statistical rectangular charts; S2. Adjust the weight based on the initial imbalance of the rotor according to the statistical rectangular diagram; S3. Adjust the dynamic balance of the rotor based on the equivalent plane.
[0019] In the specific implementation, Figures 1 to 4As shown in Figure 1, in S1, the collection and arrangement of raw data: combining the vibration characteristics exhibited during the aircraft engine test, the assembly characteristics of the compressor rotor discs at each stage, and the mass distribution characteristics of the compressor rotor, the parameters that affect the balance result of the compressor rotor are selected, as follows: the counterweight position of each stage of the compressor rotor disc, the number of counterweights of each stage of the compressor rotor disc, the initial unbalance amount of the equivalent plane, the initial unbalance angle of the equivalent plane, the circumferential runout of the compressor rotor, and the high point position of the compressor rotor runout.
[0020] In this embodiment, the six parameters collected above are introduced into a specially designed statistical matrix diagram for display.
[0021] In S2, the initial unbalance adjustment of the rotor based on the statistical matrix diagram: the change of the initial unbalance is achieved by adjusting the counterweights on each stage of the compressor rotor. The principle of adjusting the counterweights should correspond to the vibration characteristics of the aircraft engine during the test run. The vibration characteristics of a certain type of aircraft engine during the test run are large vibration and vibration jump. The counterweight adjustment of the compressor rotor should be carried out based on the vibration characteristics.
[0022] The weights of the rotor of the compressor of this type of aircraft engine are distributed on the first, third, fourth and sixth stages of the rotor. The adjustment of the first and third stage weights is more sensitive to the vibration response. Therefore, for the large vibration characteristics, only the fourth and sixth stage weights are adjusted; for the vibration jump characteristics, only the first and third stage weights are adjusted. When adjusting the weights, refer to the statistical matrix established in step one.
[0023] In S3, dynamic balancing of the rotor based on the equivalent plane: according to the adjusted initial unbalance amount, the weight is equivalently increased or decreased on the compressor rotor to achieve the purpose of further reducing the unbalance amount of the compressor rotor.
[0024] It should be pointed out that Figure 1 The concentric rings in the middle interface represent the disks of each stage of the compressor rotor; the squares in the rings represent the positions where the counterweights can be placed; the red crosshairs are the rectangular coordinate system, which divides the disks of each stage into four quadrants; the vector curve at the origin of the coordinate system can show the size and angle of the imbalance of the compressor rotor equivalent plane; the edge of the ring can show the circular runout and position of the compressor rotor.
[0025] Specific operation steps: After inputting the counterweight position of each level of the disc, the rotor runout and angle, the angle and size of the unbalance, click "with recommended counterweight picture" in the interface to complete the calculation of equivalent flexible balance and generate the final result, such as Figure 4 shown.
[0026] If you click "No recommended weight image" in the interface after entering the relevant parameters, only the original information of the compressor rotor will be generated.
[0027] in Figure 4The inner black circle is the existing counterweight on the compressor rotor, the green square is the counterweight that needs to be added after the equivalent flexible balancing algorithm, the blue triangle on the edge of the figure is the runout position of the compressor rotor, and the black parallelogram at the origin of the coordinate system is the initial imbalance of the rotor.
[0028] Finally, it should be noted that the above are only preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.
Claims
1. An equivalent flexible balance model suitable for aircraft engine maintenance, characterized in that: Including product visualization module, rotor data extraction and visualization module, balance calculation and construction guidance module; The product visualization module is used to collect and visualize the positions of the counterweights of each stage, the size and angle of the unbalance of the equivalent plane, and the position of the compressor rotor circular runout; The rotor data extraction and visualization module is used to capture the balance characteristics and quality records in the work card system and complete the automatic input of data; The balance calculation and construction guidance module forms the balance weight position and data based on the input product data and equivalent flexible balance calculation.
2. An equivalent flexible balance method suitable for aircraft engine maintenance is implemented based on an equivalent flexible balance model suitable for aircraft engine maintenance, characterized in that: The following steps are involved: S1. Collect and organize the original data of aircraft engines and establish statistical rectangular charts; S2. Adjust the weight based on the initial imbalance of the rotor in the statistical rectangular diagram; S3. Adjust the dynamic balance of the rotor based on the equivalent plane.
3. The equivalent flexible balancing method for aircraft engine maintenance according to claim 2, characterized in that: In S1, the parameters that affect the balance result of the compressor rotor are selected based on the vibration characteristics exhibited during the aircraft engine test, the assembly characteristics of the compressor rotor discs at each stage, and the mass distribution characteristics of the compressor rotor.
4. The equivalent flexible balancing method for aircraft engine maintenance according to claim 3, characterized in that: In S1, the parameters include the counterweight position of each stage of the compressor rotor disk, the number of counterweights of each stage of the compressor rotor disk, the initial unbalance amount of the equivalent plane, the initial unbalance angle of the equivalent plane, the circular runout of the compressor rotor and the high point position of the compressor rotor runout.
5. The equivalent flexible balancing method suitable for aircraft engine maintenance according to claim 3, characterized in that: In S2, the change of the initial unbalance is achieved by adjusting the counterweights on each stage of the compressor rotor disk, and the adjustment principle of the counterweights corresponds to the vibration characteristics exhibited during the aircraft engine test in S1.
6. The equivalent flexible balancing method suitable for aircraft engine maintenance according to claim 2, characterized in that: In S3, according to the adjusted initial unbalance amount, the counterweight of the compressor rotor is equivalently increased or decreased to further reduce the unbalance amount of the compressor rotor.