Blisk damage area secondary linear friction welding repair method

Abstract

The application discloses a method for repairing a damaged area of a blisk by secondary linear friction welding, and relates to the technical field of repairing key components of an aero-engine. The blisk damaged after linear friction welding is detected to determine a damaged area, and the damaged area is cut by selecting a repairing cutting mode. A linear cutting surface is processed to form a welding reference surface. A repairing patch is prepared, and the blisk after cutting is subjected to secondary linear friction welding based on the welding reference surface by using the repairing patch. The secondary linear friction welding seam area and the secondary linear friction welding surface are respectively subjected to intermediate stress relief treatment and surface finishing. A repairing part is obtained and is subjected to profiling finishing until the blisk restores to the original profile of the blade. Performance detection is performed on the blisk, and the repairing part meeting the given design and airworthiness requirements is used as the repaired blisk. The repairing joint performance reaches or approaches the level of the base material, and the use requirements of key components of the aero-engine are met.

Description

Technical Field

[0001] This invention belongs to the field of repair technology for key components of aero-engines, specifically relating to a secondary linear friction welding repair method for the damaged area of ​​an integral bladed disk. Background Technology

[0002] As a key rotating component in advanced aero-engines, integral bladed disks (IBDs) offer advantages such as integrated structure, lightweight design, and high efficiency. However, because the blades are integrally formed with the disk, if the blades are damaged during manufacturing or service due to improper transportation or impact from foreign objects, traditional repair methods are insufficient for effective repair, leading to the scrapping of the IBD, resulting in high costs and delivery delays.

[0003] Currently, integral bladed disks are mostly manufactured using linear friction welding (LFW). This process has advantages such as high weld quality and good joint strength, but there is still a lack of mature and engineering-applicable repair processes for repairing damage to integral bladed disks that have already been welded or are in service. Especially in situations where there is no welding process station or structural constraints, how to achieve high-quality secondary linear friction welding repair is a current technical challenge. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides a secondary linear friction welding repair method for the damaged area of ​​an integral bladed disk. This method is applicable to the repair process of integral bladed disks made of materials such as TC4 titanium alloy after blade damage occurs during welding or service. By simulating real welding conditions, the feasibility of repair at different repair locations (weld area, heat-affected zone, and weld center) is studied, so as to achieve the performance of the repaired joint reaching or approaching the level of the base material and meeting the usage requirements of key components of aero-engines.

[0005] The technical solution of this invention is as follows: On the one hand, a method for secondary linear friction welding repair of the damaged area of ​​an integral bladed disk is provided, the specific steps of which include: Damage detection is performed on the integral bladed disk that has been damaged after linear friction welding to determine the damaged area. A repair cutting method is selected to cut the damaged area, and the missing area after cutting is taken as the cutting defect area. At the same time, a straight cutting surface is formed, and the straight cutting surface is processed to form a welding reference surface, resulting in an integral bladed disk including the cutting defect area and the welding reference surface. A repair patch is prepared using a material that is completely consistent with the substrate material of the integral bladed disk including the cutting defect area and the welding reference surface. The repair patch has an end face, and the outline of the repair patch is completely matched with the cutting defect area. The end face is a complete single flat plane, and its geometric dimensions are completely identical to those of the welding reference surface, and the surfaces fit together.

[0006] Based on the welding reference plane, a secondary linear friction weld is performed on the entire bladed disk, including the cut defect area and the welding reference plane, using repair patches to obtain the secondary linear friction weld area and the secondary linear friction weld surface.

[0007] Intermediate stress relief treatment was performed on the weld area of ​​the secondary linear friction weld, and the surface of the weld area of ​​the secondary linear friction weld was finely repaired to obtain the repaired part.

[0008] The repaired part is subjected to contour finishing until it restores the original blade profile. The performance of the repaired part after contour finishing is then tested. The repaired part that meets the given design and airworthiness requirements is taken as the final repaired integral bladed disk.

[0009] Furthermore, the process of performing damage detection on the integral bladed disk that has undergone linear friction welding and subsequently shows signs of damage, identifying the damaged area, selecting a repair cutting method to cut the damaged area, and using the missing area after cutting as the cutting defect area, while simultaneously forming a straight cutting surface, and processing the straight cutting surface to form a welding reference surface, resulting in an integral bladed disk including the cutting defect area and the welding reference surface, specifically includes: The integral bladed disk that has been damaged after linear friction welding includes the original linear friction weld area; the original linear friction weld area includes the base material area, the heat-affected zone and the weld center.

[0010] First, ultrasonic C-scan and industrial CT are used to detect damage to the entire bladed disk, determine the damaged area, locate the damaged area, clarify the crack propagation boundary of the damaged area, and thus determine the extent of the defect.

[0011] Then, the original linear friction weld area is used as the cutting area; different cutting methods are selected according to the crack propagation boundary of the damaged area to cut the damaged area in the cutting area, forming a straight cutting surface, and obtaining an integral bladed disk with a cut defect area.

[0012] The specific rules for selecting the repair and cutting method are as follows: if the crack propagation boundary of the damaged area is outside the original linear friction weld area, select method one for repair and cutting; if the crack propagation boundary of the damaged area is located at the center of the weld, select method two for repair and cutting; if the damaged area is located in the heat-affected zone, select method three for repair and cutting; if the crack propagation boundary of the damaged area exists in multiple areas in the base material area, the weld center, and the heat-affected zone, use method four for cutting.

[0013] Method 1: Cut within the parent material area.

[0014] Method 2: Cut at the center of the weld.

[0015] Method 3: Cut within the heat-affected zone.

[0016] Method 4: Cut straight through in one go, removing all damaged areas spanning the base material area, heat-affected zone, and weld center, without retaining any local residual defect tissue.

[0017] Finally, the straight-line cut surface is machined to form the welding reference surface.

[0018] Furthermore, based on the welding reference plane, the entire bladed disk, including the cut defect area and the welding reference plane, is subjected to secondary linear friction welding using repair patches to obtain the secondary linear friction weld area and the secondary linear friction weld surface, specifically including: Using the welding reference surface as the interface between the repair patch and the integral bladed disk, which includes the cut defect area and the welding reference surface, the repair patch and the integral bladed disk, which includes the cut defect area and the welding reference surface, are precision machined and formed into a straight butt joint with equal thickness at the interface using tooling positioning and clamping. Then, a secondary linear friction welding is performed using high-frequency and low-amplitude parameters to obtain the secondary linear friction weld area. The high-frequency and low-amplitude parameters refer to the vibration frequency being higher than the set 40Hz and the vibration amplitude being lower than 0.15mm in the secondary linear friction welding execution parameters.

[0019] The specific parameters for secondary linear friction welding are as follows: welding pressure: 5~10 MPa; vibration frequency: 40~60 Hz; vibration amplitude: 0.05~0.15 mm; friction time: 2~5 s; upsetting pressure: 12~20 MPa; upsetting holding time: 15~30 s.

[0020] Furthermore, the intermediate stress relief treatment of the secondary linear friction weld area and the surface finishing of the secondary linear friction weld area to obtain the repaired part specifically include: The intermediate stress relief treatment refers to vacuum stress relief aging treatment.

[0021] The fine finishing of the surface of the secondary linear friction weld area refers to the process of removing the burrs, oxide layer and local unwelded defect layer on the surface of the secondary linear friction weld area by micro-milling after the intermediate stress relief treatment of the secondary linear friction weld area, forming a finely finished secondary linear friction weld area, and using the entire bladed disk containing the finely finished secondary linear friction weld area as the repair part.

[0022] Furthermore, the repaired component undergoes contour finishing until it restores the original blade profile, and the finished component is subjected to performance testing. The repaired component that meets the given design and airworthiness requirements is selected as the final repaired integral bladed disk. Specifically, this includes: The performance testing of the repaired parts after contour finishing includes fluorescent flaw detection, X-ray detection, three-coordinate dimensional detection, and tensile and fatigue performance testing.

[0023] Based on the performance test results, determine whether the repaired part after contour finishing meets the given design and airworthiness requirements: If the repaired part after contour finishing meets the given design and airworthiness requirements, then the repaired part including the repaired area is taken as the final repaired integral bladed disk; if the repaired part after contour finishing only fails to meet the design and airworthiness requirements in terms of dimensional accuracy or blade profile, return to perform fine finishing on the surface of the secondary linear friction weld area; if the repaired part after contour finishing has defects exceeding the set size, secondary crack propagation, or residual deteriorated tissue in the cut defect area, return to perform damage detection on the current repaired part, determine the damaged area, and select a repair cutting method to cut the damaged area until the current repaired part after contour finishing meets the given design and airworthiness requirements, thus obtaining the final repaired integral bladed disk.

[0024] On the other hand, this application proposes an electronic device, including: one or more processors, and a memory for storing instructions, which, when executed by the one or more processors, cause the one or more processors to perform the aforementioned method for secondary linear friction welding repair of a damaged area of ​​an integral bladed disk.

[0025] Thirdly, this application proposes a computer-readable storage medium storing executable instructions that, when executed, cause a processor to perform the aforementioned method for secondary linear friction welding repair of a damaged area in an integral bladed disk.

[0026] Fourthly, this application proposes a computer program product, including a computer program or instructions, which, when executed by a processor, implements the aforementioned method for secondary linear friction welding repair of the damaged area of ​​an integral bladed disk.

[0027] The beneficial effects of this invention are: 1. This invention employs differentiated cutting of weld seams to prevent the inheritance of repair defects at the source. Existing secondary repair methods use a uniform cutting approach, failing to differentiate the microstructure and properties of the primary weld base material area, heat-affected zone, and weld center. This easily leads to problems such as residual old defects, superimposed degradation of old and new microstructures, and insufficient interfacial bonding strength. This invention matches a specific cutting process to the damage location, precisely and thoroughly removing cracks, fatigue damage, and the original weld defect layer, preserving the high-quality base material to the maximum extent. This ensures a completely clean and homogeneous bonding of the secondary welding interface, significantly improving the basic quality of the weld formation.

[0028] 2. High-frequency, low-amplitude optimized welding parameters induce strong plastic rheology, dynamic grain recrystallization, and uniform diffusion of alloying elements at the secondary welding interface. Compared to traditional repair welding and single-stage friction welding, this method can eliminate latent defects such as incomplete fusion, microcracks, and inclusions. Simultaneously, it refines the grains in the weld and heat-affected zone, reconstructs a uniform microstructure, and resolves the problem of uneven microstructure in the primary welding, resulting in a repaired joint strength that is essentially close to that of the base material.

[0029] 3. By coupling vacuum stress relief with interface finishing, precise control of stress and deformation during secondary repair is achieved. Repeated welding repairs are prone to irreversible damage such as stress accumulation, expansion of the heat-affected zone, roughening of the substrate, and deformation exceeding tolerances. Vacuum aging technology stabilizes the residual stress from secondary welding within set standards; combined with micro-milling finishing to remove the surface oxide layer and stress concentration defects, the width of the heat-affected zone and the amount of welding deformation are controlled within set standards, effectively avoiding coarsening and deterioration of the base material, and balancing repair precision and structural stability.

[0030] 4. This method is applicable to the repair of integral bladed disks made of titanium alloys such as TC4, TC11, and TiAl, as well as high-temperature alloys. It has strong process adaptability and good material compatibility. After repair, the performance of the blades meets the aviation airworthiness and maintenance standards, and it has good prospects for engineering applications. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the microstructure of the original linear friction weld seam region in an embodiment of the present invention; Figure 2 This is a schematic diagram of the original linear friction welding position in an embodiment of the present invention.

[0032] Among them, 1-original linear friction weld area, 1-1-base material area, 1-2-heat affected zone, 1-3-weld center; 2-blade after cutting. Detailed Implementation

[0033] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0034] Example 1: A method for repairing the damaged area of ​​an integral bladed disk using secondary linear friction welding includes the following steps: Step 1: Perform damage inspection on the integral bladed disk that has undergone linear friction welding and subsequently shows signs of damage. Identify the damaged area and select a repair cutting method to cut it. The missing area after cutting is designated as the cutting defect area, and a straight cutting surface is formed. This straight cutting surface is then processed to create a welding reference surface, resulting in an integral bladed disk including the cutting defect area and the welding reference surface. The integral bladed disk that has undergone linear friction welding and subsequently shows signs of damage includes the original linear friction weld area. The original linear friction weld area is identified by the degree of corrosion, such as... Figure 1As shown, it includes the base material area, the heat-affected zone, and the weld center.

[0035] Specifically, the following steps are taken: First, ultrasonic C-scan and industrial CT are used to detect damage to the entire bladed disk, determine the damaged area, and accurately locate the damaged area, that is, to clarify the crack propagation boundary of the damaged area and thus determine the extent of the defect.

[0036] Then, the original linear friction weld area is used as the cutting area; different cutting methods are selected according to the crack propagation boundary of the damaged area to cut the damaged area, forming a straight cutting surface, thus obtaining an integral bladed disk with a cut defect area, such as... Figure 2 As shown.

[0037] The specific rules for selecting the repair cutting method are as follows: If the crack propagation boundary of the damaged area is located outside the original linear friction weld area, method one is selected for repair cutting to facilitate secondary welding; if the crack propagation boundary of the damaged area is located at the center of the weld, method two is selected for repair cutting; if the damaged area is located in the heat-affected zone, method three is selected for repair cutting; if the crack propagation boundary of the damaged area exists in multiple areas in the base material area, the weld center, and the heat-affected zone, method four is used for cutting.

[0038] Method 1: Cut within the parent material area.

[0039] Method 2: Cut at the center of the weld.

[0040] Method 3: Cut within the heat-affected zone.

[0041] Method 4: Cut straight through in one go, removing all damaged areas spanning the base material area, heat-affected zone, and weld center, without retaining any local residual defect tissue.

[0042] Finally, the straight-line cut surface is machined to form the welding reference surface.

[0043] In this embodiment, the flatness of the welding reference surface is controlled to be ≤0.02 mm and the surface roughness is controlled to be ≤0.02 mm. satisfy Parallelism of mating surfaces ≤ 0.01 mm.

[0044] In this embodiment, the TC4 titanium alloy integral bladed disk used in a certain type of aero-engine experienced a transverse fracture in the middle of its blade during service. The damaged length was 15 mm and the height was 20 mm. The damaged body was completely removed by a five-axis linkage CNC machining equipment, and the measured flatness of the first-level welding reference surface was 0.018 mm, which met the process requirements.

[0045] Step 2: Prepare a repair patch using a material that is completely consistent with the material of the integral bladed disk substrate, including the cut defect area and the welding reference surface; the repair patch has an end face, and the outline of the repair patch is completely matched with the cut defect area; the end face is a complete single flat plane, which is perfectly conformally matched with the geometric dimensions of the welding reference surface and fits surface to surface.

[0046] In this embodiment, the repair patch is made of TC4 titanium alloy or high-temperature alloy material with the same material as the base. The outline of the repair patch is precisely matched with the cut defect area, and the gap between the end face and the welding reference surface is ≤0.01 mm, ensuring high-precision fit of the welding interface.

[0047] Step 3: Based on the welding reference plane, use the repair patch to perform secondary linear friction welding on the entire bladed disk, including the cut defect area and the welding reference plane, to obtain the secondary linear friction welding weld area and the secondary linear friction welding surface.

[0048] Specifically, the welding reference surface is used as the interface between the repair patch and the overall bladed disk, including the cut defect area and the welding reference surface. At the interface, the tooling positioning and clamping method is used to perform precision machining and straight butt joint of the repair patch and the overall bladed disk, including the cut defect area and the welding reference surface, with equal thickness. Then, high frequency and low amplitude parameters are used for secondary linear friction welding to obtain the secondary linear friction weld area.

[0049] The high-frequency low-amplitude parameters refer to the vibration frequency being higher than the set 40Hz and the vibration amplitude being lower than 0.15mm in the secondary linear friction welding execution parameters. Specifically, the secondary linear friction welding execution parameters are: welding pressure: 5~10 MPa; vibration frequency: 40~60Hz; vibration amplitude: 0.05~0.15 mm; friction time: 2~5 s; upsetting pressure: 12~20 MPa; upsetting holding time: 15~30s.

[0050] In this embodiment, high-frequency, low-amplitude secondary linear friction welding is implemented, and tooling positioning and clamping are adopted to ensure that the gap between the end face of the repair patch and the welding reference surface is ≤0.01 mm, with no gaps, misalignments, or local suspensions on the entire end face, providing a high-precision assembly foundation for uniform friction vibration and overall synchronous plastic deformation.

[0051] Secondary linear friction welding is suitable for multi-zone composite substrates with existing primary weld structures. It adopts a high-frequency, low-amplitude, low-pressure, slow friction, and precise upsetting process mode. Through 40~60 Hz high-frequency micro-amplitude vibration, plastic frictional heat generation and metal rheology occur uniformly and synchronously in the flat bonding interface, avoiding the defects of local overheating, rheological inhomogeneity, and local incomplete welding caused by uneven interface structure in traditional processes. Secondary linear friction welding causes plastic flow and element re-diffusion of the bonding interface metal, realizing the densification and homogenization of the bonding interface, and completely eliminating defects that may exist in the welding process.

[0052] Step 4: Perform intermediate stress relief treatment on the secondary linear friction weld area and refine the surface of the secondary linear friction weld area to obtain the repaired part.

[0053] The intermediate stress relief treatment refers to performing vacuum stress relief aging treatment to reduce residual stress.

[0054] The fine finishing of the surface of the secondary linear friction weld area refers to the process of removing the burrs, oxide layer and local unwelded defect layer on the surface of the secondary linear friction weld area by micro-milling after the intermediate stress relief treatment of the secondary linear friction weld area, forming a finely finished secondary linear friction weld area. The entire bladed disk containing the finely finished secondary linear friction weld area is used as a repair part, and its flatness is controlled to be ≤0.015 mm.

[0055] In this embodiment, for TC4 alloy, the parameters for vacuum stress relief aging treatment include: temperature 600±20℃, holding time 2 hours, and furnace cooling to room temperature.

[0056] Step 5: Perform contour finishing on the repaired part until it restores the original blade profile, and conduct performance testing on the repaired part after contour finishing. The repaired part that meets the given design and airworthiness requirements is taken as the final repaired integral bladed disk.

[0057] The performance testing of the repaired parts after contour finishing includes fluorescent flaw detection, X-ray detection, three-coordinate dimensional detection, and tensile and fatigue performance testing.

[0058] Based on the performance test results, determine whether the repaired part after contour finishing meets the given design and airworthiness requirements: If the repaired part after contour finishing meets the given design and airworthiness requirements, then the repaired part including the repaired area is taken as the final repaired integral bladed disk; if the repaired part after contour finishing only fails to meet the design and airworthiness requirements in terms of dimensional accuracy or blade profile, return to step 4, and re-finish the weld surface of the secondary linear friction weld area to correct the dimensional deviation. No secondary welding is required to avoid ineffective heat input damaging the substrate; if the repaired part after contour finishing has a large defect range, secondary crack propagation, or residual deteriorated tissue in the cut defect area, return to step 1, perform damage detection on the current repaired part, determine the damaged area, and select a repair cutting method to cut the damaged area until the current repaired part after contour finishing meets the given design and airworthiness requirements, thus obtaining the final repaired integral bladed disk.

[0059] In this embodiment, for repair parts with large defect ranges, secondary crack propagation, or residual deteriorated tissue in the cut defect area after contour finishing, the process returns to step 1 to re-perform non-destructive damage verification and full-area straight cutting. After thoroughly removing the failed tissue, the patch preparation, welding, stress relief, and finishing processes are completed in sequence.

[0060] In this embodiment, a five-axis CNC machine tool was used to perform contour machining on the repair area. The test results showed that the tensile strength of the repaired joint reached 935MPa, the welding deformation was 0.025mm, and all non-destructive test results were qualified. The repair quality fully meets the structural integrity and service performance requirements of aero-engine blades.

[0061] This embodiment effectively eliminates welding defects such as incomplete welding and cracks through linear friction welding, reducing the defect rate by more than 92% and significantly improving the density and integrity of the joint. The tensile strength of the repaired joint reaches more than 95% of that of the base material (e.g., the strength of a TC4 titanium alloy joint is ≥920MPa), and the fatigue life is increased by 60%, meeting the requirements of aero-engines for high strength and high durability. Through vacuum stress relief treatment and optimized welding parameters, the residual stress is reduced to below 320MPa, the welding deformation is controlled within 0.03mm, the width of the heat-affected zone is ≤1.2mm, and the base material microstructure does not show obvious coarsening, maintaining good microstructural stability. This method is applicable to the repair of integral bladed disks of titanium alloys such as TC4, TC11, and TiAl, as well as high-temperature alloys. It has strong process adaptability and good material compatibility. After repair, all performance characteristics of the blades meet the aviation airworthiness and maintenance standards, showing good engineering application prospects.

[0062] Example 2: This embodiment proposes an electronic device, including: one or more processors, and a memory, wherein the memory is used to store instructions, and when the instructions are executed by the one or more processors, the one or more processors execute the aforementioned method for secondary linear friction welding repair of the damaged area of ​​an integral bladed disk.

[0063] The electronic device can be a mobile phone, computer, or tablet computer, etc., and includes a memory and a processor. The memory stores a computer program, which, when executed by the processor, implements a secondary linear friction welding repair method for the damaged area of ​​an integral bladed disk as described in the embodiment. It is understood that the electronic device may also include an input / output (I / O) interface and communication components.

[0064] The processor is used to execute all or part of the steps in the secondary linear friction welding repair method for the damaged area of ​​an integral bladed disk as described in the above embodiments. The memory is used to store various types of data, which may include, for example, instructions for any application or method in the electronic device, as well as application-related data.

[0065] The processor can be implemented as an Application Specific Integrated Circuit (ASIC), Digital Signal Processor (DSP), Programmable Logic Device (PLD), Field Programmable Gate Array (FPGA), controller, microcontroller, microprocessor, or other electronic components, and is used to execute the secondary linear friction welding repair method for the overall bladed disk damage area described in the above embodiments.

[0066] Example 3: This embodiment proposes a computer-readable storage medium that stores executable instructions. When these instructions are executed, if they are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium.

[0067] The computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the secondary linear friction welding repair method for the damaged area of ​​an integral bladed disk as described in the various embodiments of this application.

[0068] The aforementioned storage media include: flash memory, hard disk, multimedia card, card-type memory (e.g., SD (Secure Digital Memory Card) or DX (Memory Data Register, MDR) memory), random access memory (RAM), static random-access memory (SRAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), programmable read-only memory (PROM), magnetic storage, disk, optical disk, server, APP (Application) application store, and other media capable of storing program verification codes. These media store computer programs, which, when executed by a processor, can implement the various steps of the aforementioned method for secondary linear friction welding repair of the damaged area of ​​an integral bladed disk.

[0069] Example 4: This embodiment proposes a computer program product, including a computer program or instructions, which, when executed by a processor, implements the aforementioned method for secondary linear friction welding repair of the damaged area of ​​an integral bladed disk.

[0070] Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or part of the technical solution, can be embodied in the form of a computer program product.

[0071] The various embodiments in this application are described in a progressive manner. The same or similar parts between the various embodiments can be referred to each other. Each embodiment focuses on describing the differences from other embodiments.

[0072] The scope of protection of this application is not limited to the embodiments described above. Obviously, those skilled in the art can make various modifications and variations to this disclosure without departing from the scope and spirit of this disclosure. If such modifications and variations fall within the scope of this disclosure and its equivalents, then the intent of this disclosure also includes these modifications and variations.

Claims

1. A method for repairing the damaged area of ​​an integral bladed disk using secondary linear friction welding, characterized in that, The specific steps include: Damage detection is performed on the integral bladed disk that has been damaged after linear friction welding. The damaged area is identified and a repair cutting method is selected to cut the damaged area. The missing area after cutting is taken as the cutting defect area. At the same time, a straight cutting surface is formed. The straight cutting surface is processed to form a welding reference surface, resulting in an integral bladed disk that includes the cutting defect area and the welding reference surface. Repair patches are prepared using a material that is completely identical to the material of the integral bladed disk substrate, including the cut defect area and the welding reference surface; the repair patches have end faces, and the outline of the repair patches is completely matched with the cut defect area; the end faces are complete single straight planes, and are perfectly conformally matched with the geometric dimensions of the welding reference surface and fit surface to surface; Based on the welding reference plane, the entire bladed disk, including the cut defect area and the welding reference plane, is subjected to secondary linear friction welding using repair patches to obtain the secondary linear friction weld area and the secondary linear friction weld surface. Intermediate stress relief treatment was performed on the weld area of ​​the secondary linear friction weld, and the surface of the weld area of ​​the secondary linear friction weld was finely repaired to obtain the repaired part; The repaired part is subjected to contour finishing until it restores the original blade profile. The performance of the repaired part after contour finishing is then tested. The repaired part that meets the given design and airworthiness requirements is taken as the final repaired integral bladed disk.

2. The method for secondary linear friction welding repair of the damaged area of ​​an integral bladed disk according to claim 1, characterized in that, The process involves damage detection of the integral bladed disk that has undergone linear friction welding and subsequently shows signs of damage. The damaged area is identified, and a repair cutting method is selected to cut it. The missing area after cutting is designated as the cutting defect area. A straight cutting surface is formed, and this surface is then processed to create a welding reference surface, resulting in an integral bladed disk comprising the cutting defect area and the welding reference surface. Specific steps include: The integral bladed disk that has been damaged after linear friction welding includes the original linear friction weld area; the original linear friction weld area includes the base material area, the heat-affected zone and the weld center. First, ultrasonic C-scan and industrial CT are used to detect damage to the entire bladed disk, determine the damaged area, locate the damaged area, clarify the crack propagation boundary of the damaged area, and thus determine the extent of the defect. Then, the original linear friction weld area is used as the cutting area; different cutting methods are selected according to the crack propagation boundary of the damaged area to cut the damaged area in the cutting area, forming a straight cutting surface, and obtaining an integral bladed disk with a cut defect area; The specific rules for selecting the repair and cutting method are as follows: If the crack propagation boundary of the damaged area is located outside the original linear friction weld area, select method one for repair and cutting; if the crack propagation boundary of the damaged area is located at the center of the weld, select method two for repair and cutting; if the damaged area is located in the heat-affected zone, select method three for repair and cutting; if the crack propagation boundary of the damaged area exists in multiple areas in the base material area, the weld center, and the heat-affected zone, use method four for cutting. Method 1: Cut within the base material area; Method 2: Cut at the center of the weld; Method 3: Cut within the heat-affected zone; Method 4: Cut straight through in one go, removing all damaged areas spanning the base material area, heat-affected zone, and weld center, without retaining any local residual defect tissue; Finally, the straight-line cut surface is machined to form the welding reference surface.

3. The method for secondary linear friction welding repair of the damaged area of ​​an integral bladed disk according to claim 1, characterized in that, Based on the welding reference plane, a secondary linear friction weld is performed on the entire bladed disk, including the cut defect area and the welding reference plane, using repair patches to obtain the secondary linear friction weld area and the secondary linear friction weld surface. The specific steps include: Using the welding reference surface as the interface between the repair patch and the integral bladed disk, including the cut defect area and the welding reference surface, the repair patch and the integral bladed disk, including the cut defect area and the welding reference surface, are precision machined and formed into a straight butt joint with equal thickness using tooling positioning and clamping at the interface. Secondary linear friction welding is then performed using high-frequency, low-amplitude parameters to obtain the secondary linear friction weld area. The high-frequency, low-amplitude parameters refer to the vibration frequency being higher than the set 40Hz and the vibration amplitude being lower than 0.15mm in the secondary linear friction welding execution parameters. The specific parameters for secondary linear friction welding are as follows: welding pressure: 5~10 MPa; vibration frequency: 40~60 Hz; vibration amplitude: 0.05~0.15 mm; friction time: 2~5 s; upsetting pressure: 12~20 MPa; upsetting holding time: 15~30 s.

4. The method for secondary linear friction welding repair of the damaged area of ​​an integral bladed disk according to claim 1, characterized in that, The process of performing intermediate stress relief treatment on the secondary linear friction weld area and fine-tuning the surface of the secondary linear friction weld area to obtain a repaired part specifically includes: The intermediate stress relief treatment refers to vacuum stress relief aging treatment; The fine finishing of the surface of the secondary linear friction weld area refers to the process of removing the burrs, oxide layer and local unwelded defect layer on the surface of the secondary linear friction weld area by micro-milling after the intermediate stress relief treatment of the secondary linear friction weld area, forming a finely finished secondary linear friction weld area, and using the entire bladed disk containing the finely finished secondary linear friction weld area as the repair part.

5. The method for secondary linear friction welding repair of the damaged area of ​​an integral bladed disk according to claim 1, characterized in that, The process involves contour machining of the repaired component until it restores the original blade profile, followed by performance testing of the machined component. The repaired component that meets the given design and airworthiness requirements is selected as the final repaired bladed disk. Specifically, this includes: The performance testing of the repaired parts after contour finishing includes fluorescent flaw detection, X-ray detection, three-coordinate dimensional detection, and tensile and fatigue performance testing. Based on the performance test results, determine whether the repaired part after contour finishing meets the given design and airworthiness requirements: If the repaired part after contour finishing meets the given design and airworthiness requirements, then the repaired part including the repaired area is taken as the final repaired integral bladed disk; if the repaired part after contour finishing only fails to meet the design and airworthiness requirements in terms of dimensional accuracy or blade profile, return to perform fine finishing on the surface of the secondary linear friction weld area; if the repaired part after contour finishing has defects exceeding the set size, secondary crack propagation, or residual deteriorated tissue in the cut defect area, return to perform damage detection on the current repaired part, determine the damaged area, and select a repair cutting method to cut the damaged area until the current repaired part after contour finishing meets the given design and airworthiness requirements, thus obtaining the final repaired integral bladed disk.

6. An electronic device, characterized in that, The device includes one or more processors and a memory for storing instructions that, when executed by the one or more processors, cause the one or more processors to perform a secondary linear friction welding repair method for the damaged area of ​​an integral bladed disk as described in any one of claims 1-5.

7. A computer-readable storage medium, characterized in that, It stores executable instructions that, when executed, cause the processor to perform a secondary linear friction welding repair method for the damaged area of ​​an integral bladed disk as described in any one of claims 1-5.

8. A computer program product, characterized in that, Includes a computer program or instructions that, when executed by a processor, implement the secondary linear friction welding repair method for the damaged area of ​​an integral bladed disk as described in any one of claims 1-5.

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