Method, apparatus, and electronic device for aeroengine blade fatigue strengthening

Abstract

The application provides a method for aero-engine blade fatigue strengthening, comprising: performing modal analysis on an aero-engine blade model to obtain a stress concentration area position; planning a numerical control machining path according to the stress concentration area position, and taking the numerical control machining path as a fatigue strengthening path; and controlling an ultrasonic strengthening device to travel along the numerical control machining path according to set machining parameters, so as to fatigue strengthen the stress concentration area. The surface stress concentration area of the aero-engine blade under a service environment is obtained through low-frequency modal analysis, and the ultrasonic strengthening device is locally strengthened in a numerical control machining mode, so that targeted strengthening is realized and the control precision is improved.

Description

Technical Field

[0001] This application relates to the field of aero-engine manufacturing technology, specifically to a method, apparatus, and electronic equipment for fatigue strengthening of aero-engine blades. Background Technology

[0002] When aero-engine blades operate under extreme environmental conditions combining high speed, high pressure, and complex vibration (or high temperature), fatigue failure can occur due to defects in their surface integrity. This ultimately leads to the propagation of microcracks in the fatigue-prone areas of the blade, and may even result in blade fracture. Existing data indicates that over 80% of fatigue cracks in aero-engine blades originate from surface processing defects or damage, such as cutting marks, surface microcracks, surface strain hardening, surface microstructure damage, and surface tensile stress. Rough surfaces or surface damage can cause high levels of surface stress concentration, thus becoming fatigue sources. Hidden microstructural and micromechanical damage defects in the subsurface layer can rapidly accelerate crack formation and propagation, thereby accelerating fatigue failure. Therefore, employing effective surface treatment and strengthening processes to control surface integrity is crucial for improving the fatigue life of aero-engine blades and ensuring the long-term reliable operation of aero-engines. Summary of the Invention

[0003] To address the problems of low control accuracy, the need for additional processing, and unsuitability for thin-walled parts in existing aero-engine blade fatigue strengthening methods, this application provides an improved aero-engine blade fatigue strengthening method, apparatus, and electronic equipment.

[0004] According to a first aspect of this application, a method for fatigue strengthening of aero-engine blades is provided, comprising:

[0005] Modal analysis was performed on an aero-engine blade model to determine the location of stress concentration regions.

[0006] A CNC machining path is planned based on the location of the stress concentration area, and the CNC machining path is used as a fatigue strengthening path.

[0007] The ultrasonic strengthening device is controlled to move along the CNC machining path according to the set machining parameters, thereby strengthening the stress concentration area through fatigue.

[0008] According to some embodiments of this application, the modal analysis of the aero-engine blade model to obtain the location of stress concentration regions includes:

[0009] The stress distribution results were obtained by simulating and analyzing the aero-engine blade model using low-frequency modes.

[0010] The location of the stress concentration region is obtained based on the stress distribution results.

[0011] According to some embodiments of this application, the step of using low-frequency modes to perform simulation analysis on the aero-engine blade model to obtain stress distribution results includes:

[0012] First-order low-frequency modal analysis and second-order low-frequency modal analysis were performed on the aero-engine blade model to obtain stress distribution cloud maps.

[0013] According to some embodiments of this application, the modal analysis of the aero-engine blade model to obtain the location of stress concentration regions further includes:

[0014] In the modal analysis, the boundary conditions are set to the two mounting planes of the fixed tenon.

[0015] According to some embodiments of this application, the stress concentration area includes both ends of the connection between the tenon and the blade.

[0016] According to some embodiments of this application, the method further includes:

[0017] The location of the stress concentration area is recorded and saved using the spatial coordinates on the blade.

[0018] According to some embodiments of this application, controlling the ultrasonic strengthening device to travel along the CNC machining path according to set machining parameters includes:

[0019] The ultrasonic strengthening device is controlled to be positioned in the normal direction of the processed surface.

[0020] According to some embodiments of this application, the processing parameters include:

[0021] Prestress: 2-6KN, ultrasonic frequency: 20-40KHz, amplitude: 2μm-6μm, feed rate: 1m / min-3m / min, rotation speed: 1500-3000 rpm, row spacing: 0.05-0.2mm.

[0022] According to another aspect of this application, an apparatus for fatigue strengthening of aero-engine blades is also provided, comprising:

[0023] The modal analysis module is used to perform modal analysis on aero-engine blade models to obtain the location of stress concentration regions.

[0024] The path planning module is used to plan a CNC machining path based on the location of the stress concentration area, and to use the CNC machining path as a fatigue strengthening path.

[0025] The strengthening implementation module is used to control the ultrasonic strengthening device to move along the CNC machining path according to the set processing parameters, thereby strengthening the stress concentration area through fatigue.

[0026] According to another aspect of this application, an electronic device for fatigue strengthening of aero-engine blades is also provided, comprising:

[0027] One or more processors;

[0028] Storage device for storing one or more programs;

[0029] When the one or more programs are executed by the one or more processors, the one or more processors implement the above method.

[0030] The method, apparatus, and electronic equipment for fatigue strengthening of aero-engine blades provided in this application obtain the stress concentration area on the surface of aero-engine blades under service environment through low-frequency modal analysis, and use it as the target strengthening area for planning the CNC machining path; control the ultrasonic strengthening equipment to perform ultrasonic strengthening on the stress concentration area along the planned CNC machining path according to the set machining parameters, thereby realizing precise targeted ultrasonic strengthening of the fatigue dangerous area of ​​aero-engine blades and improving the fatigue life of the blades. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings, without exceeding the scope of protection claimed by this application.

[0032] Figure 1 A flowchart of a method for fatigue strengthening of aero-engine blades according to an example embodiment of this application is shown;

[0033] Figure 2 A schematic diagram of an aero-engine blade model according to an example embodiment of this application is shown;

[0034] Figure 3 A schematic diagram of the simulation analysis boundary condition settings according to an example embodiment of this application is shown;

[0035] Figure 4A A schematic diagram of the first-order low-frequency modal simulation analysis results according to an example embodiment of this application is shown on the XY plane;

[0036] Figure 4B A schematic diagram of the first-order low-frequency modal simulation analysis results according to an example embodiment of this application is shown on the ZY plane;

[0037] Figure 5A A schematic diagram of the second-order low-frequency modal simulation analysis results according to an example embodiment of this application is shown on the XY plane;

[0038] Figure 5B A schematic diagram showing the simulation analysis results of the second-order low-frequency modes according to an example embodiment of this application is displayed on the ZY plane.

[0039] Figure 6A A schematic diagram of the blade-side stress distribution in first-order low-frequency modal analysis according to an example embodiment of this application is shown.

[0040] Figure 6B A schematic diagram of the stress distribution on the back side of the blade in a first-order low-frequency modal analysis according to an example embodiment of this application is shown.

[0041] Figure 7 A flowchart of a method for fatigue strengthening of aero-engine blades according to another exemplary embodiment of this application is shown;

[0042] Figure 8 A schematic diagram of the blade model mesh generation result according to an example embodiment of this application is shown;

[0043] Figure 9 A schematic diagram showing a comparison of surface hardness before and after surface strengthening using the method for fatigue strengthening of aero-engine blades according to an example embodiment of this application is shown.

[0044] Figure 10 A schematic diagram showing a comparison of the residual stress field depth before and after surface strengthening using a method for fatigue strengthening of aero-engine blades according to an example embodiment of this application is shown.

[0045] Figure 11 A block diagram of an apparatus for fatigue strengthening of aero-engine blades according to an example embodiment of this application is shown;

[0046] Figure 12 A block diagram of an apparatus for fatigue strengthening of aero-engine blades according to another exemplary embodiment of this application is shown;

[0047] Figure 13 A schematic diagram of an electronic device according to an example embodiment of this application is shown. Detailed Implementation

[0048] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0049] The terms "first," "second," etc., used in this application are used to distinguish different objects, not to describe a predetermined order. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to these processes, methods, products, or apparatuses.

[0050] In this document, the term "embodiment" means that a predetermined feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0051] Currently, fatigue strengthening of blade surfaces is typically achieved through surface treatment processes, primarily shot peening and laser shock peening. Shot peening involves bombarding the blade surface with a large number of shot particles to generate residual compressive stress, thus strengthening the blade. However, shot peening suffers from low control precision and can cause surface unevenness or localized deformation, increasing surface roughness. Subsequent vibratory finishing is required to improve this roughness, but this process reduces the residual compressive stress generated during strengthening, thereby decreasing fatigue life. When laser shock peening is applied to thin-walled parts (e.g., aircraft blades), the impact compression wave penetrates the material and reflects tensile waves on the free surface, generating residual tensile stress within the material. Furthermore, the reflected tensile wave couples with the incident wave, creating a complex residual stress distribution that affects the strengthening effect. Additionally, deformation of thin-walled parts during laser shock peening cannot be ignored.

[0052] To address the shortcomings of existing fatigue strengthening methods, such as low control accuracy, the need for additional post-processing, and unsuitability for thin-walled parts, this application provides an improved fatigue strengthening method for aero-engine blades. This method involves simulating the service environment of an aero-engine blade, performing finite element analysis on a blade model, and accurately determining the stress concentration region and stress distribution map based on the modal analysis results. Based on the obtained stress concentration region and stress distribution map, a CNC machining path is determined. Furthermore, an ultrasonic strengthening device connected to the CNC machining equipment is used to locally ultrasonically strengthen the stress concentration region along the planned CNC machining path. On the one hand, the simulation of the real service environment and corresponding modal analysis enables precise identification of the stress concentration region, achieving accurate targeted strengthening. On the other hand, surface strengthening via ultrasonic strengthening using CNC machining along the machining trajectory not only increases surface compressive stress but also further enhances the accuracy of surface strengthening through precise control of the strengthening path.

[0053] Figure 1 A flowchart illustrating a method for fatigue strengthening of aero-engine blades according to an example embodiment of this application is shown. According to an example embodiment of this application, the method for fatigue strengthening of aero-engine blades provided by this application includes the following steps.

[0054] In step S110, modal analysis is performed on the aero-engine blade model to obtain the location of stress concentration regions.

[0055] To accurately strengthen the fatigue areas of aero-engine blades, in the example embodiments of this application, modal analysis is performed on the established finite element model of the aero-engine blade to locate the fatigue-prone areas. For example, a model such as... Figure 2 The image shows a model of an aero-engine blade.

[0056] During the service life of aero-engine blades, the blades are connected to the turbine disk via tenons. In the example implementation of this application, in order to more realistically simulate the service environment of aero-engine blades, that is, to simulate the motion state of the blades during use, tenon boundary conditions can be set during the modal analysis in step S110. That is, the two mounting planes of the tenon are fixed, so that the tenon bears the load generated by the blade vibration in the modal analysis. Figure 3 A schematic diagram of the simulation analysis boundary condition settings according to an example embodiment of this application is shown. By setting the tenon boundary condition, excessive bending or twisting of the blade during modal analysis can be avoided, thereby improving the reliability and accuracy of the modal analysis results.

[0057] In the example embodiments of this application, low-frequency modal analysis is used to simulate and analyze the stress distribution of an aero-engine blade model. Modal analysis reveals the vibration type and frequency of the aero-engine blade during service, as well as the stress concentration areas at the corresponding natural vibration frequencies, thereby locating potential fatigue hazard areas. In modal analysis, low-frequency modes, due to their lower frequency, longer vibration period, and longer response time to external excitation signals, are more susceptible to excitation from the aero-engine's operating conditions and environment, resulting in vibration modes with larger amplitudes and greater effective mass (i.e., the mass involved in a specific vibration mode of the structure). In a vibration system, the greater the effective mass of a vibration mode, the more significant its impact on the entire system. Therefore, using low-frequency modal analysis more closely approximates the actual service environment of aero-engine blades and can more accurately reflect the impact on blade performance.

[0058] In the example embodiments of this application, first-order low-frequency modal analysis and second-order low-frequency modal analysis can be performed on the aero-engine blade model to obtain stress distribution cloud maps. For example, first-order low-frequency modal analysis can obtain the first-order mode shape and first-order deformation of the blade under service conditions. Figure 4A and 4B A schematic diagram of the simulation analysis results for the first-order low-frequency mode is shown. (For example...) Figure 4A and 4B As shown, the first mode shape is the mode shape of the blade under free bending. The maximum amplitude of the vibration is located at the diagonal position of the blade, and the relative displacement is greater the farther away from the root. The maximum value is 347.1 mm. The second mode shape and second deformation of the blade under service conditions can be obtained through second-order low-frequency modal analysis. Figure 5A and 5B A schematic diagram of the simulation analysis results for the second-order low-frequency mode is shown. (For example...) Figure 5A and 5B As shown, the second-order vibration mode is a torsional vibration mode; see [link / reference]. Figure 5A and 5B It is evident that the blade cross section undergoes reverse shear deformation of more than one wavelength, resulting in significant changes in local stress distribution and displacement trends in multiple regions. The region with the maximum displacement is located at the blade tip, with a value of 582.4 mm.

[0059] Furthermore, during first-order and second-order low-frequency modal analyses, corresponding stress distribution cloud maps can be obtained, which can be used to determine the location of stress concentration regions. Taking first-order low-frequency modal analysis as an example, refer to... Figure 6A and 6BAs shown in the first-order stress distribution cloud map, the stress concentration area is located at both ends of the tenon-blade connection. This area exhibits high stress, with the stress decreasing further away from the tenon. This indicates that the connection area between the tenon and blade is most prone to failure. Similarly, the stress distribution in the second-order stress distribution cloud map follows the same trend as the first-order map, with the area of ​​maximum stress still being the connection between the tenon and blade. Furthermore, the stress value is greater than that in the first-order mode, further confirming that the stress concentration area is located at the connection point between the tenon and blade, which is the most likely place for failure. Therefore, by obtaining the stress distribution results through first-order and second-order low-frequency modal analysis, we can identify the area of ​​maximum stress and high failure risk—the stress concentration area.

[0060] Subsequently, the identified stress concentration areas can be designated as the fatigue-prone areas of the blades under service conditions, and the spatial coordinates on the blades can be used to record and save the locations of the identified stress concentration areas, thereby providing targeted strengthening targets for subsequent ultrasonic shock strengthening.

[0061] In step S120, a CNC machining path is planned based on the location of the stress concentration area, and this CNC machining path is used as the fatigue strengthening path. In an example embodiment of this application, in order to perform precise targeted strengthening, a machining path is planned using CNC machining based on the coordinate point data of the stress concentration area, and strengthening is implemented by controlling the strengthening device to move along the machining path. For example, the CNC machining path can be a surface trajectory planned on the located fatigue-prone area of ​​the blade. During implementation, the CNC machining route can be planned based on the obtained coordinates of the fatigue-prone area of ​​the blade on the blade model body.

[0062] In step S130, the ultrasonic strengthening device is controlled to move along the CNC machining path according to the set machining parameters, thereby strengthening the stress concentration area through fatigue.

[0063] In ultrasonic impact strengthening, ultrasonic vibration applies impact loading to the structural surface, forcing plastic deformation and refining the material grains, thereby increasing surface hardness and generating a beneficial residual compressive stress layer, ultimately extending the fatigue life of the structure. During the strengthening process, the ultrasonic strengthening device can be connected to a CNC machine tool and controlled to move along the CNC machining path while remaining aligned with the normal direction of the machined surface, thus targeting and strengthening stress concentration areas. In this process, machining parameters can be adjusted in real-time to ensure precise control of the strengthening path and improve strengthening quality. In the example implementation of this application, the machining parameters can be selected as follows: prestress: 2-6KN, ultrasonic frequency: 20-40KHz, amplitude: 2μm-6μm, feed rate: 1m / min-3m / min, rotation speed: 1500-3000 rpm, and line spacing: 0.05-0.2mm.

[0064] In the strengthening process of this embodiment, high-power ultrasound can be used as the driving energy. An ultrasonic transducer converts electrical energy into mechanical energy, which is then transmitted to the fatigue-prone surface of the blade through the high-intensity vibration of the impactor. The high-intensity vibration contact between the impactor and the blade surface within a small space causes plastic deformation on the lower surface of the blade, forming a hardened layer. This localized plastic deformation increases the density of lattice defects and creates macroscopic residual compressive stress. This surface modification reduces stress concentration and crack initiation points on the fatigue-prone surface of the blade, thereby reducing crack propagation rate and fatigue damage. The residual compressive stress can counteract the tensile stress generated during external loading, thus slowing crack propagation and delaying fatigue failure. The residual compressive stress can also improve the material's resistance to stress corrosion, reducing corrosion-induced crack formation. Ultimately, this achieves the goal of extending the fatigue life of engine blades and ensuring the long service life of aero-engines.

[0065] Figure 7 A flowchart of a method for fatigue strengthening of aero-engine blades according to another exemplary embodiment of this application is shown.

[0066] According to an example embodiment of this application, before performing modal analysis, step S100 may be included: meshing the aero-engine blade model. In the example embodiment of this application, tetrahedral meshes can be used for meshing. The number of meshes can be 35153, and the number of meshes is increased for complex-shaped tenons and blade connections to achieve more accurate calculation precision. The element type can be C3D10 using higher-order shape functions; C3D10 elements using higher-order shape functions can provide higher calculation precision than lower-order elements and exhibit better robustness in handling nonlinear problems; it can still be well applied to strongly nonlinear conditions such as large deformation and contact, thus being suitable for the blade service environment. Figure 8The diagram shown is a schematic representation of the mesh generation result of a blade model according to an example embodiment of this application.

[0067] Figure 9 A schematic diagram showing a comparison of surface hardness before and after surface strengthening using the method for fatigue strengthening of aero-engine blades according to an example embodiment of this application is shown. Figure 10 A schematic diagram showing a comparison of the residual stress field depth before and after surface strengthening using a method for fatigue strengthening of aero-engine blades according to an example embodiment of this application is presented.

[0068] See Figure 9 and Figure 10 Through experimental verification, the method for fatigue strengthening of aero-engine blades provided in this application can effectively improve surface hardness and deepen the depth of surface residual stress field, thereby effectively improving the fatigue life and surface quality of aero-engine blades, as shown in Table 1 below.

[0069] Table 1. Comparison of fatigue life of aero-engine blades before and after ultrasonic strengthening.

[0070]

[0071] Figure 11 A block diagram of an apparatus for fatigue strengthening of aero-engine blades according to an example embodiment of this application is shown.

[0072] According to an example embodiment of this application, an apparatus for fatigue strengthening of aero-engine blades is also provided. See also Figure 11 The device 300 includes a modal analysis module 310, a path planning module 320, and a strengthening implementation module 330. The modal analysis module 310 performs modal analysis on an aero-engine blade model to obtain the location of stress concentration areas. The path planning module 320 plans a CNC machining path based on the location of the stress concentration areas and uses this CNC machining path as a fatigue strengthening path. The strengthening implementation module 330 controls the ultrasonic strengthening device to move along the CNC machining trajectory according to set machining parameters, thereby performing fatigue strengthening on the stress concentration areas.

[0073] Figure 12 A block diagram of an apparatus for fatigue strengthening of aero-engine blades according to another exemplary embodiment of this application is shown.

[0074] In an example embodiment of this application, the apparatus 300 may further include a mesh generation module 340. The mesh generation module 340 is used to mesh the aero-engine blade model before performing modal analysis. For example, a tetrahedral mesh can be used for mesh generation, with a mesh number of 35153 and an element type of C3D10 using higher-order shape functions.

[0075] Figure 13 A block diagram of an electronic device according to an example embodiment of this application is shown.

[0076] This application also provides an electronic device 700 for fatigue strengthening of aero-engine blades. Figure 12 The electronic device 700 shown is merely an example and should not impose any limitations on the functionality and scope of use of the embodiments of this application.

[0077] like Figure 12 As shown, the electronic device 700 is presented in the form of a general-purpose computing device. The components of the electronic device 700 may include, but are not limited to: at least one processing unit 710, at least one storage unit 720, and a bus 730 connecting different system components (including the storage unit 720 and the processing unit 710).

[0078] The storage unit 720 stores program code, which can be executed by the processing unit 710, causing the processing unit 710 to perform the methods described in the above embodiments of this application.

[0079] Storage unit 720 may include readable media in the form of volatile storage units, such as random access memory (RAM) 7201 and / or cache memory 7202, and may further include read-only memory (ROM) 7203.

[0080] The storage unit 720 may also include a program / utility 7204 having a set (at least one) program module 7205, such program module 7205 including but not limited to: an operating system, one or more application programs, other program modules and program data, each or some combination of these examples may include an implementation of a network environment.

[0081] Bus 730 can represent one or more of several types of bus structures, including a memory cell bus or memory cell controller, a peripheral bus, a graphics acceleration port, a processing unit, or a local bus using any of the various bus structures.

[0082] Electronic device 700 can also communicate with one or more external devices 7001 (e.g., touchscreen, keyboard, pointing device, Bluetooth device, etc.), and with one or more devices that enable a user to interact with electronic device 700, and / or with any device that enables electronic device 700 to communicate with one or more other computing devices (e.g., router, modem, etc.). This communication can be performed via input / output (I / O) interface 750. Furthermore, electronic device 700 can also communicate with one or more networks (e.g., local area network (LAN), wide area network (WAN), and / or public networks, such as the Internet) via network adapter 760. Network adapter 760 can communicate with other modules of electronic device 700 via bus 730. It should be understood that, although not shown in the figures, other hardware and / or software modules can be used in conjunction with electronic device 700, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems.

[0083] In addition, this application also provides a computer-readable medium having a computer program stored thereon, which, when executed by a processor, implements the above-described method for fatigue strengthening of aero-engine blades.

[0084] The method, apparatus, and electronic equipment for fatigue strengthening of aero-engine blades provided in this application obtain the stress concentration area on the surface of aero-engine blades under service environment through low-frequency modal analysis, and use it as the target strengthening area for planning the CNC machining path; control the ultrasonic strengthening equipment to perform ultrasonic strengthening on the stress concentration area along the planned CNC machining path according to the set machining parameters, thereby realizing precise targeted ultrasonic strengthening of the fatigue dangerous area of ​​aero-engine blades and improving the fatigue life of the blades.

[0085] The embodiments of this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are only for the purpose of helping to understand the method and core ideas of this application. Furthermore, any changes or modifications made by those skilled in the art based on the ideas of this application, and on the specific implementation methods and application scope of this application, are all within the scope of protection of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

Claims

1. A method for fatigue strengthening of aero-engine blades, characterized in that, The method includes: Modal analysis was performed on an aero-engine blade model to determine the location of stress concentration regions. The location of the stress concentration area is recorded and saved using the spatial coordinates on the blade; A CNC machining path is planned based on the location of the stress concentration area, and the CNC machining path is used as a fatigue strengthening path. The ultrasonic strengthening device is controlled to move along the CNC machining path according to the set machining parameters, thereby strengthening the stress concentration area through fatigue. The processing parameters include: Prestress: 2-6KN, ultrasonic frequency: 20-40KHz, amplitude: 2μm-6μm, feed rate: 1m / min-3m / min, rotation speed: 1500-3000 rpm, row spacing: 0.05-0.2mm; The modal analysis of the aero-engine blade model to obtain the location of stress concentration regions includes: In the modal analysis, the boundary conditions are set to the two mounting planes of the fixed tenon.

2. The method according to claim 1, characterized in that, The modal analysis of the aero-engine blade model to obtain the location of stress concentration regions includes: The stress distribution results were obtained by simulating and analyzing the aero-engine blade model using low-frequency modes. The location of the stress concentration region is obtained based on the stress distribution results.

3. The method according to claim 2, characterized in that, The stress distribution results obtained by simulating and analyzing the aero-engine blade model using low-frequency modes include: First-order low-frequency modal analysis and second-order low-frequency modal analysis were performed on the aero-engine blade model to obtain stress distribution cloud maps.

4. The method according to any one of claims 1-3, characterized in that, The stress concentration areas are located at both ends of the connection between the tenon and the blade.

5. The method according to any one of claims 1-3, characterized in that, The control of the ultrasonic enhancement device to travel along the CNC machining path according to the set machining parameters includes: The ultrasonic strengthening device is controlled to be positioned in the normal direction of the processed surface.

6. A device for fatigue strengthening of aero-engine blades, characterized in that, include: The modal analysis module is used to perform modal analysis on aero-engine blade models to obtain the location of stress concentration regions. The path planning module is used to plan a CNC machining path based on the location of the stress concentration area, and to use the CNC machining path as a fatigue strengthening path. The strengthening implementation module is used to control the ultrasonic strengthening device to move along the CNC machining path according to the set processing parameters, thereby strengthening the stress concentration area through fatigue. The processing parameters include: Prestress: 2-6KN, ultrasonic frequency: 20-40KHz, amplitude: 2μm-6μm, feed rate: 1m / min-3m / min, rotation speed: 1500-3000 rpm, row spacing: 0.05-0.2mm; The device further includes: Module for recording and saving the location of the stress concentration area using spatial coordinates on the blade; The modal analysis module is also used for: In the modal analysis, the boundary conditions are set to the two mounting planes of the fixed tenon.

7. An electronic device for fatigue strengthening of aero-engine blades, characterized in that, include: One or more processors; Storage device for storing one or more programs; When the one or more programs are executed by the one or more processors, the one or more processors implement the method of any one of claims 1-5.

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