Aero-engine adjusting mechanism joint wear life evaluation and prediction method and system

Abstract

The invention provides an aero-engine adjusting mechanism joint wear life evaluation and prediction method and system. The prediction method comprises the steps that wear coefficients of a joint component under different working conditions are obtained through analysis based on a material-level wear prediction model; establishing a three-dimensional wear prediction mathematical model of the joint component by using the wear prediction model and a function relationship between different working conditions and wear coefficients; establishing a multi-body dynamic model for representing the characteristics of the joint components, and acquiring motion characteristic parameters of the joint components; inputting the motion characteristic parameters into a three-dimensional wear prediction mathematical model to obtain a single wear value at the current moment; the single-time abrasion value serves as input, the structural size of the joint component is modified, the modified size parameter of the joint component is input into the multi-body dynamic model, the motion characteristic parameter of the next moment is obtained, the cycle is repeated till the abrasion value is larger than the abrasion threshold value, and then the theoretical service life of the joint component is obtained. The method is used for accurately obtaining the theoretical life of the joint component.

Description

Technical Field

[0001] The present invention relates to the technical field of wear life prediction of aero-engine components, and particularly to a method and system for evaluating and predicting the wear life of a joint of an aero-engine regulating mechanism. Background Art

[0002] Various motion regulating mechanisms of aero-engines, such as a compressor stator vane regulating mechanism, a thrust reverser actuating mechanism, an open rotor pitch-changing mechanism, etc., are important components for improving the stable operating range of the engine and are widely used in modern aero-engines. Once the motion regulating mechanism fails during flight, it will cause a decrease in the performance of the aero-engine or a serious flight accident.

[0003] The motion mechanism of an aero-engine is a multi-body complex system composed of multiple components connected by mechanical joints. Taking the compressor adjustable stator vane regulating mechanism as an example, the shaft-bushing is the most important joint kinematic pair, and there is a relative rotational motion relationship between the shaft and the bushing, and this kinematic pair is also called a revolute pair. Due to its working characteristics, the adjustable stator vane regulating mechanism has different service characteristics in static and dynamic conditions. It is affected by non-stationary airflow in the static condition and has fretting wear phenomenon; in the dynamic condition, the shaft-bushing has sliding wear damage.

[0004] The service space of the regulating mechanism is narrow and the working conditions are harsh. The clearance hinge pair of the shaft-bushing cannot realize in-situ wear detection, resulting in great randomness in the current replacement of the shaft-bushing and being unable to achieve a balance between economy and service safety.

[0005] Based on this, the inventors of the present application designed a method and system for evaluating and predicting the wear life of a joint of an aero-engine regulating mechanism to overcome the above technical problems. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to provide a method and system for evaluating and predicting the wear life of a joint of an aero-engine regulating mechanism to overcome the defect of great difficulty in predicting the wear life of joint components in the prior art.

[0007] The present invention solves the above technical problem by the following technical solutions:

[0008] The present invention provides a method for evaluating and predicting the wear life of a joint of an aero-engine regulating mechanism, which is characterized by including:

[0009] Step 1, analyzing and obtaining the wear coefficient of the joint component under different working conditions based on a material-level wear prediction model;

[0010] Step 2, establishing a three-dimensional wear prediction mathematical model of the joint component by using the wear prediction model and the functional relationship between different working conditions and the wear coefficient;

[0011] Step 3: Establish a multi-body dynamics model characterizing the characteristics of the joint component and obtain the motion characteristic parameters of the joint component;

[0012] Step 4: Input the motion characteristic parameters into the three-dimensional wear prediction mathematical model to obtain the single wear value at the current moment;

[0013] Step 5: Use the single wear value as the input to modify the structural dimensions of the joint component. The dimension parameters of the modified joint component are input into the multi-body dynamics model to obtain the motion characteristic parameters at the next moment. Repeat this process until the wear value is greater than the wear threshold, and then obtain the theoretical life of the joint component.

[0014] According to an embodiment of the present invention, the step 1 includes:

[0015] Step 11: Use a pin-on-disc friction and wear testing machine to test and evaluate the anti-wear performance of the joint component material specimens under different working conditions;

[0016] Step 12: Analyze the wear coefficients of the material specimens under different working conditions based on the material-level wear prediction model.

[0017] According to an embodiment of the present invention, the step 2 includes:

[0018] First, perform data fitting and expansion on the wear coefficients to establish a functional correspondence between different working conditions and wear coefficients;

[0019] Combine the wear prediction model and the functional correspondence between different working conditions and wear coefficients to establish a three-dimensional wear prediction mathematical model of the joint component.

[0020] According to an embodiment of the present invention, the step 3 includes:

[0021] 31. Select the material of the joint component according to the service conditions of the joint component and the anti-wear performance of the material;

[0022] 32. Obtain the load-bearing law of the joint component under static and dynamic conditions through numerical calculation and simulation;

[0023] 33. Establish the multi-body dynamics model characterizing the characteristics of the joint component.

[0024] According to an embodiment of the present invention, the motion characteristic parameters of the joint component include the contact collision force, contact area, and sliding speed of the joint component.

[0025] According to an embodiment of the present invention, the multi-body dynamics model is composed of a contact collision force model, a friction force model, and a flexible beam model.

[0026] According to an embodiment of the present invention, the wear threshold is determined according to the service conditions of the joint component.

[0027] The present invention also provides an evaluation system for the joint wear life of an aero-engine regulating mechanism. The evaluation system for the joint wear life of an aero-engine regulating mechanism is characterized in that the evaluation system for the joint wear life of an aero-engine regulating mechanism adopts the evaluation and prediction method for the joint wear life of an aero-engine regulating mechanism as described above. The evaluation system includes:

[0028] An analysis module, which analyzes and obtains the wear coefficient of the joint component under different working conditions based on the material-level wear prediction model;

[0029] A connection module, which uses the wear prediction model and the functional relationship between different working conditions and the wear coefficient to establish a three-dimensional wear prediction mathematical model of the joint component;

[0030] A building module, which builds a multi-body dynamics model characterizing the characteristics of the joint component and obtains the motion characteristic parameters of the joint component;

[0031] A calculation module, which inputs the motion characteristic parameters into the three-dimensional wear prediction mathematical model to obtain the single wear value at the current moment;

[0032] An output module, which takes the single wear value as an input, modifies the structural dimensions of the joint component, inputs the dimension parameters of the modified joint component into the multi-body dynamics model, obtains the motion characteristic parameters at the next moment, and loops until the wear value is greater than the wear threshold, thereby obtaining the theoretical life of the joint component.

[0033] The present invention also provides an electronic device, which is characterized in that it includes a processor and a memory. The memory stores a program or instruction that can run on the processor, and the program or instruction is executed by the processor to implement the evaluation and prediction method for the joint wear life of an aero-engine regulating mechanism according to any one of claims 1-7.

[0034] The present invention also provides a readable storage medium, which is characterized in that a program or instruction is stored on the readable storage medium, and the program or instruction, when executed by a processor, implements the evaluation and prediction method for the joint wear life of an aero-engine regulating mechanism according to any one of claims 1-7.

[0035] The positive and progressive effects of the present invention are as follows:

[0036] The method and system for evaluating and predicting the joint wear life of an aero-engine regulating mechanism according to the present invention are based on relevant knowledge of tribology and dynamics. By combining simulation, theoretical analysis, and experimental exploration, a numerical calculation method for predicting the wear of the kinematic pair of the joint of the motion regulating mechanism is established, providing a basis for the life evaluation and replacement of the actual kinematic pair, reducing the cost of aero-engine users, and improving the service safety of aero-engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The above and other features, properties, and advantages of the present invention will become more apparent from the following description in conjunction with the drawings and embodiments, wherein:

[0038] Figure 1 is a flowchart of the method for evaluating and predicting the joint wear life of the aero-engine regulating mechanism according to the present invention;

[0039] Figure 2 is a schematic structural diagram of the electronic device according to the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0040] In order to make the above objects, features, and advantages of the present invention more obvious and understandable, the following detailed description of the specific embodiments of the present invention will be given in conjunction with the drawings.

[0041] Embodiments of the present invention will now be described in detail with reference to the drawings. Preferred embodiments of the present invention will now be described in detail, and examples thereof are shown in the drawings. In all possible cases, the same reference numerals will be used throughout the drawings to represent the same or similar parts. In addition, although the terms used in the present invention are selected from well-known and commonly used terms, some of the terms mentioned in the specification of the present invention may be selected by the applicant according to his or her judgment, and their detailed meanings are described in the relevant parts of the present description. In addition, it is required to understand the present invention not only by the actual terms used, but also by the meaning implied by each term.

[0042] Please refer to Figure 1 , the present invention provides a method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism, including:

[0043] S1. Analyze and obtain the wear coefficients of joint components under different working conditions based on the material-level wear prediction model.

[0044] It should be noted that the joint components of the present invention are described by taking a rotating shaft and a bushing as examples, but are not limited thereto.

[0045] First, use a pin-on-disc friction and wear testing machine to test and evaluate the anti-wear performance of the joint component material specimens under different working conditions.

[0046] Different working conditions include but are not limited to: different temperatures, loads, sliding speeds, etc. The joint components can be the rotating shaft and bushing as described above.

[0047] Then, based on the material-level wear prediction model, such as the Archard model, analyze and obtain the wear coefficients of the specimens under different working conditions.

[0048] Furthermore, using machine learning methods, perform data fitting and extension on the above limited wear coefficients to establish the functional correspondence between different working conditions and wear coefficients. For example: n = w(T, P, V). Where, n is the wear coefficient, T is the temperature, P is the load, and V is the sliding speed.

[0049] S2. Use the wear prediction model and the functional relationship between different working conditions and the wear coefficient to establish a three-dimensional wear prediction mathematical model for the joint components.

[0050] That is, based on the finite element idea, combine the wear prediction model and the functional relationship between different working conditions and wear coefficients to establish a three-dimensional wear prediction mathematical model for the joint components.

[0051] The three-dimensional wear prediction mathematical model is as follows:

[0052]

[0053] Among them, i represents the three directions of x, y, and z; h represents the wear depth; m is the functional relationship for calculating single wear, which is mainly related to the contact pressure, speed, and wear coefficient; Δt is a small time.

[0054] S3. Establish a multi-body dynamics model characterizing the characteristics of the joint components and obtain the motion characteristic parameters of the joint components.

[0055] It should be noted that according to the service conditions of the engine regulating mechanism and the anti-wear performance of its materials, select the materials of the joint components, and then through numerical calculation and simulation, obtain the load law of the joint components under static and dynamic conditions, that is, the external load.

[0056] Combined with the multi-body dynamics modeling idea, establish a multi-body dynamics model that can characterize the characteristics of the joint components. Among them, the characteristics of the joint components include but are not limited to: rigid-flexible characteristics, structural characteristics, temperature characteristics, etc., which are not limited here.

[0057] Specifically, the above-mentioned dynamics modeling idea is:

[0058] Adopt the natural node coordinate method to characterize the kinematic relationship of each component of the engine regulating mechanism, that is, the constraint equation.

[0059] For its rigid-flexible characteristics, the absolute node coordinate method can be used for characterization, that is, use the Euler-Bernoulli beam to characterize its flexible beam structure characteristics.

[0060] For the adjustment mechanism system with multiple joint pair clearance structural features, a contact collision force model and a friction force model are used for characterization. The contact collision force model is as follows:

[0061]

[0062] The friction force model is characterized by the LuGre model, and its relationship is:

[0063]

[0064] Among them, Δ is the elastic deformation amount between two components (component i, component j) of the joint kinematic pair, h i 、h j are the material properties of component i and component j, R i and R j are the radii of component i and component j, is the elastic deformation speed, is the speed of starting elastic deformation, c e is the recovery coefficient of the material, σ 0 is the rigidity coefficient of the material, σ 1 is the damping coefficient, σ 2 is the viscous friction coefficient, v t is the relative sliding speed, z is the average deformation amount, is the speed of the deformation amount.

[0065] Its elastic deformation amount Δ can be determined by calculating the center point positions of the pin shaft and the bushing, and has the following relationship:

[0066]

[0067] Furthermore, since the joint components are at different temperatures, the temperature characteristics can be added to the internal elastic force in its flexible characteristics. The temperature characteristics are thermal deformations caused by temperature. The relationships between temperature and deformation, and between flexible deformation and internal elastic force are respectively:

[0068] ε T =α T (T - T ref );

[0069]

[0070] Among them, ε T is the thermal deformation, α T is the thermal expansion coefficient of the material, T is the temperature of the flexible unit, T ref is the reference temperature, F fis the internal elastic force matrix of the flexible component (including the elastic force generated by temperature deformation), a is the absolute nodal coordinate of the flexible component, E is the elastic modulus of the material, A is the cross-sectional area of the material, and ε l is the structural strain.

[0071] Furthermore, combining the above contact collision force model, friction force model, and flexible beam model, the multi-body dynamics model of the joint component is established by the Lagrange multiplier method as follows:

[0072]

[0073] where Mr is the mass matrix of the rigid component, Mf is the mass matrix of the flexible component, Qr is the external force matrix (loading law) of the rigid component, Qf is the external force matrix of the flexible component, u is the natural nodal coordinate of the rigid component, t is the time, is the acceleration of the natural nodal coordinate of the rigid component, is the acceleration of the absolute nodal coordinate of the flexible component, Φ(u, a, t) is the constraint matrix, is the Jacobian matrix of the constraint matrix of the rigid component with respect to the nodal coordinate of the rigid component, is the Jacobian matrix of the constraint matrix of the flexible component with respect to the nodal coordinate of the flexible component.

[0074] According to the above multi-body dynamics model, parameters such as the contact collision force, contact area, and sliding speed of the joint component can be obtained.

[0075] S4. Input the motion characteristic parameters into the three-dimensional wear prediction mathematical model to obtain the single wear value at the current moment.

[0076] That is, inputting parameters such as the contact collision force, contact area, and sliding speed into the three-dimensional wear prediction mathematical model can obtain the single wear value of the joint component at the current moment.

[0077] S5. Using the single wear value as the input, modify the structural dimensions of the joint component, input the dimension parameters of the modified joint component into the multi-body dynamics model, and obtain the motion characteristic parameters at the next moment. Repeat this process until the wear value is greater than the wear threshold, and then obtain the theoretical life of the joint component.

[0078] That is, if the current wear value is less than the wear threshold, the single - wear value is used as the input, the dimensions of the joint components of the adjustment mechanism are modified, the modified dimensions of the joint components are substituted into the multi - body dynamics model to obtain parameters such as the contact and collision force, contact area, and sliding speed after wear at the next moment, and further, the above - mentioned parameters are input into the three - dimensional wear prediction mathematical model to obtain the wear value at the next moment, and then compared with the wear threshold. This cycle continues until the wear value exceeds the wear threshold, at which point the cycle ends.

[0079] By superimposing the time experienced in the cycle, the theoretical life of the joint component from the current moment onwards can be obtained.

[0080] Furthermore, the above - mentioned wear threshold is determined based on the service conditions of the joint components.

[0081] Based on the relevant knowledge of tribology and dynamics, the present invention establishes a numerical calculation method for predicting joint wear of an aero - engine adjustment mechanism through a combination of simulation, theoretical analysis, and experimental exploration, and further obtains the life of joint components under complex static and dynamic service conditions.

[0082] The present invention can also predict and evaluate the service life of joint components under complex static and dynamic service conditions. The predicted life data can support the formulation of the replacement cycle of the joint components of the adjustment mechanism. Then, based on the joint pair replacement cycle formulated according to the predicted life, the use cost of parts can be effectively reduced, the number of repairs can be reduced, and the service safety of the aero - engine can be improved.

[0083] The present invention also proposes an aero - engine adjustment mechanism joint wear life assessment system, which is characterized in that the aero - engine adjustment mechanism joint wear life assessment system adopts the above - mentioned aero - engine adjustment mechanism joint wear life assessment and prediction method. The assessment system includes:

[0084] An analysis module for analyzing and obtaining the wear coefficient of joint components under different working conditions based on the material - level wear prediction model;

[0085] A connection module for establishing a three - dimensional wear prediction mathematical model of joint components by using the wear prediction model and the functional relationship between different working conditions and the wear coefficient;

[0086] A building module for building a multi - body dynamics model characterizing the characteristics of joint components and obtaining the motion characteristic parameters of joint components;

[0087] A calculation module for inputting the motion characteristic parameters into the three - dimensional wear prediction mathematical model to obtain the single - wear value at the current moment;

[0088] An output module, which uses the single wear value as input to modify the structural dimensions of the joint component. The dimension parameters of the modified joint component are input into the multi-body dynamics model to obtain the motion characteristic parameters at the next moment, and this cycle continues until the wear value is greater than the wear threshold, thereby obtaining the theoretical life of the joint component.

[0089] Through the above joint wear life evaluation system, the present invention can establish a numerical calculation method for predicting joint wear of an aero-engine regulating mechanism by combining simulation, theoretical analysis and experimental exploration, and obtain the life of the joint pair under complex static and dynamic service conditions.

[0090] Refer to Figure 2 , the present invention also provides an electronic device 900, including: a processor 901 and a memory 902. The memory 902 stores a program or instruction that can run on the processor 901, and the program or instruction is executed by the processor 901 to perform the above-mentioned method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism. When the program or instruction is executed by the processor 901, it realizes each process of the above-mentioned implementation manner of the method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism, and can achieve the same technical effect. To avoid repetition, it will not be described in detail here.

[0091] The present invention also provides a readable storage medium, on which a program or instruction is stored. When the program or instruction is executed by a processor, it realizes the method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism as described above. When the program or instruction is executed by the processor, it realizes each process of the above-mentioned implementation manner of the method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism, and can achieve the same technical effect. To avoid repetition, it will not be described in detail here.

[0092] For those skilled in the art, the above invention disclosure is only an example and does not constitute a limitation to this application. Although not explicitly stated here, those skilled in the art may make various modifications, improvements and corrections to this application. Such modifications, improvements and corrections are proposed in this application, so such modifications, improvements and corrections still belong to the spirit and scope of the exemplary implementation manner of this application.

[0093] At the same time, this application uses specific terms to describe the implementation manners of this application. Such as "one implementation manner", "an implementation manner", and / or "some implementation manners" mean a certain feature, structure or characteristic related to at least one implementation manner of this application. Therefore, it should be emphasized and noted that the "one implementation manner" or "an implementation manner" or "an alternative implementation manner" mentioned twice or more at different positions in this specification is not necessarily the same implementation manner. In addition, certain features, structures or characteristics in one or more implementation manners of this application can be appropriately combined.

[0094] Some aspects of the present application can be executed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above-mentioned hardware or software can all be referred to as "data blocks", "modules", "engines", "units", "components", or "systems". The processor can be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. In addition, aspects of the present application may be embodied as a computer product located on one or more computer-readable media, which includes computer-readable program code. For example, the computer-readable media may include, but is not limited to, magnetic storage devices (such as hard disks, floppy disks, magnetic tapes...), optical disks (such as compact disks CD, digital versatile disks DVD...), smart cards, and flash memory devices (such as cards, sticks, key drives...).

[0095] The computer-readable media may contain a propagated data signal that contains computer program code, for example, on a baseband or as part of a carrier wave. The propagated signal may have various forms of manifestation, including electromagnetic form, optical form, etc., or a suitable combination of forms. The computer-readable media can be any computer-readable media other than computer-readable storage media, which can be connected to an instruction execution system, apparatus, or device to implement communication, propagation, or transmission for use of the program. The program code located on the computer-readable media can be propagated through any suitable media, including radio, cable, fiber optic cable, radio frequency signal, or similar media, or any combination of the above media.

[0096] Similarly, it should be noted that, in order to simplify the description disclosed in this application and thus assist in the understanding of one or more embodiments of the invention, in the foregoing description of the embodiments of this application, multiple features are sometimes grouped into one embodiment, drawing, or description thereof. However, this disclosure method does not mean that the features required by the subject matter of this application are more than those mentioned in the claims. In fact, the features of the embodiments are fewer than all the features of the individual embodiments disclosed above. In some embodiments, numbers describing components and attribute quantities are used. It should be understood that such numbers used for the description of embodiments are modified by the modifiers "about", "approximate", or "substantially" in some examples. Unless otherwise specified, "about", "approximate", or "substantially" indicate that the numbers allow a variation of ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, and such approximate values may vary according to the characteristics required by individual embodiments. In some embodiments, the numerical parameters should consider the specified significant digits and adopt the method of retaining the general number of digits. Although the numerical ranges and parameters used in some embodiments of this application to confirm the breadth of their scope are approximate values, in specific embodiments, such numerical settings are as precise as possible within the feasible range.

[0097] Although the present invention is disclosed above in its preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, all modifications, equivalent changes, and decorations made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention fall within the protection scope defined by the claims of the present invention.

Claims

1. A method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism, characterized in that, it includes: Step 1: Analyze and obtain the wear coefficients of joint components under different working conditions based on a material-level wear prediction model; Step 2: Use the wear prediction model and the functional relationship between different working conditions and the wear coefficients to establish a three-dimensional wear prediction mathematical model for joint components; Step 3: Establish a multi-body dynamics model characterizing the characteristics of joint components and obtain the motion characteristic parameters of joint components; Step 4: Input the motion characteristic parameters into the three-dimensional wear prediction mathematical model to obtain the single wear value at the current moment; Step 5: Use the single wear value as the input to modify the structural dimensions of the joint component. The dimension parameters of the modified joint component are input into the multi-body dynamics model to obtain the motion characteristic parameters at the next moment, and so on until the wear value is greater than the wear threshold, thereby obtaining the theoretical life of the joint component.

2. The method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism according to claim 1, characterized in that, the said Step 1 includes: Step 11: Use a pin-on-disc friction and wear testing machine to test and evaluate the anti-wear performance of joint component material specimens under different working conditions; Step 12: Analyze the wear coefficients of the material specimens under different working conditions based on a material-level wear prediction model.

3. The method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism according to claim 1, characterized in that, the said Step 2 includes: First, perform data fitting and extension on the wear coefficients to establish a functional correspondence between different working conditions and wear coefficients; Combine the wear prediction model and the functional correspondence between different working conditions and wear coefficients to establish a three-dimensional wear prediction mathematical model for joint components.

4. The method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism according to claim 1, characterized in that, the said Step 3 includes:

31. Select the material of the joint component according to the service conditions of the joint component and the anti-wear performance of the material; 32. Obtain the load-bearing law of the joint component under static and dynamic conditions through numerical calculation and simulation; 33. Establish the multi-body dynamics model characterizing the characteristics of the joint component.

5. The method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism according to claim 1, characterized in that, the motion characteristic parameters of the joint component include the contact collision force, contact area and sliding speed of the joint component.

6. The method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism according to claim 1, characterized in that, the multi-body dynamics model is composed of a contact collision force model, a friction force model and a flexible beam model combined.

7. The method for evaluating and predicting the joint wear life of an aero-engine regulating mechanism according to claim 1, characterized in that, the wear threshold is determined according to the service condition of the joint component.

8. An aero-engine regulating mechanism joint wear life evaluation system, characterized in that, The joint wear life evaluation system for an aero-engine regulating mechanism adopts the aero-engine regulating mechanism joint wear life evaluation and prediction method as described in any one of claims 1-7. The evaluation system includes: An analysis module that analyzes and obtains the wear coefficients of joint components under different working conditions based on a material-level wear prediction model; A connection module that uses the wear prediction model and the functional relationship between different working conditions and the wear coefficients to establish a three-dimensional wear prediction mathematical model for joint components; A establishment module that establishes a multi-body dynamics model characterizing the characteristics of joint components and obtains the motion characteristic parameters of joint components; A calculation module that inputs the motion characteristic parameters into the three-dimensional wear prediction mathematical model to obtain the single wear value at the current moment; An output module that uses the single wear value as an input to modify the structural dimensions of the joint component. The dimension parameters of the modified joint component are input into the multi-body dynamics model to obtain the motion characteristic parameters at the next moment, and this cycle continues until the wear value is greater than the wear threshold, thereby obtaining the theoretical life of the joint component.

9. An electronic device, characterized in that, it includes: A processor and a memory. The memory stores programs or instructions that can run on the processor, and the programs or instructions are executed by the processor to implement the aero-engine regulating mechanism joint wear life evaluation and prediction method as described in any one of claims 1-7.

10. A readable storage medium, characterized in that, the readable storage medium stores programs or instructions, and when the programs or instructions are executed by a processor, they implement the aero-engine regulating mechanism joint wear life evaluation and prediction method as described in any one of claims 1-7.

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