Synchronous induction thermomagnetic auxiliary laser remanufacturing device and method for aircraft engine blade

Abstract

The invention provides an aircraft engine blade synchronous induction thermomagnetic auxiliary laser remanufacturing device and method. The laser remanufacturing device comprises a workbench, a sliding rail, a printing head, an alternating current input head and a coil. The workbench is used for mounting and fixing a to-be-repaired blade; the sliding rail is fixedly connected with the printing head; the printing head can perform multi-degree-of-freedom movement; the coil is a disc type coil, is mounted on the alternating current input head, is conductively connected with the alternating current input head and is used for performing induction heating on the repaired part of the blade to be repaired; the alternating current input head is installed on the sliding rail in a sliding mode and can be fixed to the sliding rail at a designated position. The temperature difference of a molten pool in a deposition area is reduced by increasing the temperature of a substrate and a deposition layer through coil induction heating, thermal stress is reduced, cracking is restrained, meanwhile, a to-be-deposited area is preheated to reduce the temperature difference of the molten pool in the to-be-deposited area, a deposited area is slowly cooled to slow down the gamma'phase precipitation speed, and the deposition effect is improved. And reduction of embrittlement and inhibition of formation of solid cracks are facilitated.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengine blade repair, and in particular to a synchronous induction thermomagnetic assisted laser remanufacturing device and method for aeroengine blades. Background Art

[0002] An aeroengine is an abbreviation for an aircraft engine. An aircraft engine is a national key weapon and a strategic high point for national defense security, scientific and technological strength, and the level of high-end manufacturing. The turbine blade is one of the most critical and valuable core components of an aircraft engine. The turbine blade has extremely high requirements for high-temperature strength, toughness, and fatigue performance. It mainly uses high-performance nickel-based superalloy materials, and the manufacturing process is difficult, has a long cycle, and is expensive. Key components such as turbine blades work under high temperature, high pressure, and strong centrifugal force, and are prone to wear and fatigue cracks, resulting in a service life of only 500 to 1000 hours. After reaching the service life and failing, they need to be replaced. Replacing the failed blades severely limits the economic feasibility. Therefore, someone proposed to repair the failed blades through laser remanufacturing.

[0003] Superalloys have the characteristics of high alloying and a wide solidification range. Coupled with the fact that laser remanufacturing has a large temperature gradient and an extremely high cooling rate, crack defects are extremely likely to occur in the repair area and the heat affected zone, seriously endangering the repair quality and structural integrity. Summary of the Invention

[0004] In view of this, the present invention provides a synchronous induction thermomagnetic assisted laser remanufacturing device and method for aeroengine blades to solve the technical problems mentioned in the above background art, that is, laser remanufacturing has a large temperature gradient and an extremely high cooling rate, and crack defects are extremely likely to occur in the repair area and the heat affected zone, seriously endangering the repair quality and structural integrity.

[0005] The technical solution of the present invention is realized as follows:

[0006] In the first aspect, the present invention provides a synchronous induction thermomagnetic assisted laser remanufacturing device for aeroengine blades, including a workbench, a slide rail, a printing head, an alternating current input head, and a coil, wherein:

[0007] The workbench is used for installing and fixing the blade to be repaired;

[0008] The slide rail is fixedly connected to the printing head;

[0009] The printing head can move in multiple degrees of freedom and is located above the workbench, and is used for emitting laser and spraying metal powder onto the blade to be repaired;

[0010] The coil is a disc coil, which is installed on the alternating current input head and electrically connected thereto. An avoidance area allowing the laser and metal powder to pass through is provided inside the coil, and the coil is used for induction heating of the repair part of the blade to be repaired;

[0011] The alternating current input head is slidably installed on the slide rail and can be fixed at a specified position on the slide rail to adjust the distance between the coil and the print head.

[0012] On the basis of the above technical solutions, preferably, a connecting member is further included. The connecting member is fixedly connected to the slide rail and the print head respectively, and the connecting member can move in multiple degrees of freedom.

[0013] On the basis of the above technical solutions, preferably, the coil includes a disc body, a first conductive rod and a second conductive rod; one end of the disc body close to the central axis is connected to the first conductive rod, and the end of the disc body far from the central axis is connected to the second conductive rod; both the first conductive rod and the second conductive rod are connected to the alternating current input head.

[0014] On the basis of the above technical solutions, preferably, the disc body is formed by connecting the multi-turn disc coils end to end.

[0015] On the basis of the above technical solutions, preferably, an alternating current power supply and a wire are further included, and the wire is connected to the alternating current power supply and the alternating current input head respectively.

[0016] On the basis of the above technical solutions, preferably, under the combined action of laser heating and induction heating, the powder melts on the blade to be repaired to form a molten pool, and the coil is also used for induction heating of the molten pool to control the temperature gradient and solidification rate of the molten pool.

[0017] In a second aspect, the present invention provides a method for synchronous induction thermomagnetic assisted laser remanufacturing of aero-engine blades, using the aero-engine blade synchronous induction thermomagnetic assisted laser remanufacturing device as described in the first aspect, including:

[0018] Grind off the coating of the repair part of the blade to be repaired, fix the blade to be repaired on the workbench, and adjust the position of the print head so that the initial distance is maintained between the coil and the blade to be repaired;

[0019] Configure the print head with the optimal laser processing process parameters, and configure the alternating current input head with the optimal alternating frequency and alternating input power;

[0020] Emit laser and spray metal powder onto the blade to be repaired through the print head, and the coil performs induction heating on the repair part of the blade to be repaired;

[0021] Through the synchronous movement of the coil and the print head, metal powder is gradually deposited at the repair site of the blade to be repaired.

[0022] Based on the above technical solutions, preferably, the print head is configured with the best laser processing process parameters, and the alternating current input head is configured with the optimal alternating frequency and alternating input power, including:

[0023] Determine the best laser processing process parameters according to the orthogonal experiment. The laser processing process parameters include laser power, scanning speed, and powder feeding speed;

[0024] Adopt the above best laser processing process parameters to configure the alternating frequency and alternating input power of the alternating current input head. Through the orthogonal experiment, select the optimal alternating frequency and alternating input power.

[0025] Based on the above technical solutions, preferably, the laser power is 600 - 1200W, the scanning speed is 60 - 150mm / min, and the powder feeding speed is 0.3 - 0.6L / min.

[0026] Based on the above technical solutions, preferably, the alternating frequency is 10 - 20kHz, and the alternating input power is 2 - 10kW.

[0027] The synchronous induction thermomagnetic assisted laser remanufacturing device and method for aeroengine blades of the present invention have the following beneficial effects compared with the prior art:

[0028] (1) The repair site of the blade to be repaired is induction heated through the coil. After the alternating current input head is fixed at the specified position on the slide rail, the coil and the print head move synchronously, adjusting the laser remanufacturing process plan and the induction heating assistance plan, precisely controlling the thermal field distribution, increasing the temperature of the substrate and the deposition layer to reduce the temperature difference of the molten pool in the deposition area, which helps to reduce thermal stress and inhibit cracking. At the same time, preheat the area to be deposited to reduce the temperature difference of the molten pool in the area to be deposited and slow down the cooling of the deposited area to slow down the precipitation rate of γ' phase, which is beneficial to slow down embrittlement and inhibit the formation of solid-state cracks;

[0029] (2) One end of the disk body close to the central axis is connected to the first conductive rod, and the end of the disk body far from the central axis is connected to the second conductive rod; both the first conductive rod and the second conductive rod are connected to the alternating current input head, realizing the connection fixation and conductive connection between the coil and the alternating current input head. The structure of this disk-type coil can make the magnetic field more uniform, facilitating the thermal field control of magnetic field induction heating;

[0030] (3) It is formed by connecting the ends of multiple turns of the disk body in series to form a uniform spiral distribution structure, so that the magnetic field can be more uniform, further reducing the temperature difference, helping to reduce thermal stress and inhibit cracking;

[0031] (4) The molten pool is inductively heated by the coil to regulate the temperature gradient and solidification rate of the molten pool. The heat source formed by the coil induction heating not only raises the temperature of the molten pool, reduces the temperature difference of the molten pool in the deposition area, helps to reduce thermal stress and inhibit cracking, but also preheats the area to be deposited to reduce the temperature difference of the molten pool in the area to be deposited, and cools the deposited area slowly to slow down the precipitation rate of the γ' phase, which is beneficial to slowing down embrittlement and inhibiting the formation of solid-state cracks;

[0032] (5) By regulating the laser remanufacturing process plan and the induction heating assistance plan, the thermal field and magnetic field distribution are precisely controlled. It can not only inhibit crack defects and promote the directional continuous growth of grain structure, but also bring about the refinement of the γ' strengthening phase and the formation of a dislocation network around the strengthening phase, which can improve the mechanical properties of the repair area. Description of the Drawings

[0033] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0034] Figure 1 It is a schematic structural diagram of the aero-engine blade synchronous induction thermomagnetic assisted laser remanufacturing device in the embodiment of the present invention;

[0035] Figure 2 It is a schematic flow diagram of the aero-engine blade synchronous induction thermomagnetic assisted laser remanufacturing method in the embodiment of the present invention;

[0036] Figure 3 It is a schematic diagram of the crack performance of the synchronous induction thermomagnetic assisted laser remanufacturing sample in the embodiment of the present invention;

[0037] Figure 4 It is a schematic diagram of the directional continuous growth performance of the grain structure of the synchronous induction thermomagnetic assisted laser remanufacturing sample in the embodiment of the present invention;

[0038] Figure 5 It is a schematic diagram of the influence of the synchronous induction thermomagnetic assisted laser remanufacturing on the γ' strengthening phase of the blade in the embodiment of the present invention;

[0039] Figure 6Schematic diagram of the dislocation network formed around the γ′ strengthening phase in the synchronous induction thermomagnetic assisted laser remanufacturing in the embodiment of the present invention.

[0040] Explanation of reference numerals: 1 - Workbench, 2 - Slide rail, 3 - Print head, 4 - Alternating current input head, 5 - Coil, 6 - Intermediate shaft, 7 - Connecting piece, 8 - Alternating power supply, 9 - Wire;

[0041] 100 - Blade to be repaired;

[0042] 51 - Disk body, 52 - First conductive rod, 53 - Second conductive rod. Detailed implementation manners

[0043] Next, in combination with the implementation manners of the present invention, the technical solutions in the implementation manners of the present invention will be clearly and completely described. Obviously, the described implementation manners are only a part of the implementation manners of the present invention, rather than all of the implementation manners. Based on the implementation manners in the present invention, all other implementation manners obtained by those of ordinary skill in the art without making creative efforts belong to the scope of protection of the present invention.

[0044] Referring to Figure 1-6 As shown, in the first - aspect embodiment of the present invention, a synchronous induction thermomagnetic assisted laser remanufacturing device for aero - engine blades is proposed, including a workbench 1, a slide rail 2, a print head 3, an alternating current input head 4, and a coil 5, wherein:

[0045] The workbench 1 is used for installing and fixing the blade 100 to be repaired; the coating near the repair area of the blade 100 to be repaired is ground off and fixed on the workbench 1. The blade 100 to be repaired is stably assembled on the workbench 1. The workbench 1 is placed horizontally and the blade 100 to be repaired is placed vertically;

[0046] The slide rail 2 is fixedly connected to the print head 3;

[0047] The print head 3 can move in multiple degrees of freedom and is located above the workbench 1, and is used for emitting laser and spraying metal powder onto the blade 100 to be repaired; the print head 3 is installed on the intermediate shaft 6, and the connecting piece 7 is fixedly connected to the intermediate shaft 6 and the slide rail 2 respectively to realize the fixed connection between the slide rail 2 and the print head 3. The connecting piece 7 can move in multiple degrees of freedom. By moving the connecting piece 7 according to a preset trajectory, the synchronous movement of the slide rail 2 and the print head 3 can be realized;

[0048] The coil 5 is a disk - type coil. The coil 5 is installed on the alternating current input head 4 and is electrically connected to it. An avoidance area allowing the laser and metal powder to pass through is provided inside the coil 5. The coil 5 is used for inductively heating the repair part of the blade 100 to be repaired;

[0049] The alternating current input head 4 is slidably mounted on the slide rail 2 and can be fixed to the slide rail 2 at a specified position to adjust the distance between the coil 5 and the print head 3. Slide the alternating current input head 4 on the slide rail 2 and fix it when it slides to the specified position. At this time, the distance between the coil 5 and the print head 3 is fixed. By moving the connecting member 7 along a preset trajectory, the coil 5 and the print head 3 move together.

[0050] For the aero-engine blade synchronous induction thermomagnetic-assisted laser remanufacturing device proposed in this embodiment, the repair part of the blade 100 to be repaired is inductively heated by the coil 5. After the alternating current input head 4 is fixed to the slide rail 2 at a specified position, the coil 5 and the print head 3 move synchronously to regulate the laser remanufacturing process plan and the induction heating assistance plan, precisely control the thermal field distribution, increase the temperature of the substrate and the deposition layer to reduce the temperature difference of the molten pool in the deposition area, which helps to reduce thermal stress and inhibit cracking. At the same time, preheat the area to be deposited to reduce the temperature difference of the molten pool in the area to be deposited and slow down the cooling of the deposited area to slow down the precipitation rate of the γ' phase, which is beneficial to slow down embrittlement and inhibit the formation of solid-state cracks.

[0051] In some embodiments, the coil 5 includes a disk body 51, a first conductive rod 52 and a second conductive rod 53; one end of the disk body 51 close to the central axis is connected to the first conductive rod 52, and one end of the disk body 51 far from the central axis is connected to the second conductive rod 53; both the first conductive rod 52 and the second conductive rod 53 are connected to the alternating current input head 4, and an avoidance area is formed in the inner circle of the disk body 51. After the first conductive rod 52 is connected to the inner circle of the disk body 51, it immediately extends in a direction away from the central axis of the disk body 51, and will not block the laser and metal powder passing through the avoidance area. Through the above structure, the connection and fixation and conductive connection between the coil 5 and the alternating current input head 4 are realized. The structure of this disk-type coil can make the magnetic field more uniform and facilitate the control of the thermal field of magnetic field induction heating.

[0052] In some embodiments, the disk body 51 is formed by connecting multiple turns of disk coils end to end. By forming the disk body 51 by connecting multiple turns of disk coils end to end, a uniform spiral distribution structure is formed, so that the magnetic field can be more uniform, further reducing the temperature difference, which helps to reduce thermal stress and inhibit cracking.

[0053] In some embodiments, the aero-engine blade synchronous induction thermomagnetic-assisted laser remanufacturing device further includes an alternating current power supply 8 and a wire 9, and the wire 9 is respectively connected to the alternating current power supply 8 and the alternating current input head 4. The alternating current power supply 8 uses a 380V power supply. The alternating current power supply 8 and the alternating current input head 4 are soft-connected through the wire 9, which is convenient for the movement of the alternating current input head 4 on the slide rail 2 and maintains conductive connection during the movement, improving reliability and stability.

[0054] In some embodiments, under the combined action of laser heating and induction heating, the powder melts on the blade 100 to be repaired to form a molten pool. The molten pool undergoes electromagnetic stirring under the action of an induction magnetic field and gradually cools and solidifies during the movement of the coil 5 and the print head 3. The coil 5 is also used to perform induction heating on the molten pool to regulate the temperature gradient and solidification rate of the molten pool. By performing induction heating on the molten pool through the coil 5 to regulate the temperature gradient and solidification rate of the molten pool, the heat source formed by the induction heating of the coil 5 not only increases the temperature of the molten pool, reduces the temperature difference of the molten pool in the deposition area, helps reduce thermal stress and inhibit cracking, but also preheats the area to be deposited to reduce the temperature difference of the molten pool in the area to be deposited, and slow-cools the deposited area to slow down the precipitation rate of the γ' phase, which is beneficial to slowing down embrittlement and inhibiting the formation of solid-state cracks.

[0055] Based on the same concept, in the embodiment of the second aspect of the present invention, as shown in Figure 2 a method for synchronous induction thermomagnetic-assisted laser remanufacturing of aero-engine blades is provided. Using the aero-engine blade synchronous induction thermomagnetic-assisted laser remanufacturing device described in the embodiment of the first aspect, it includes:

[0056] Step S1: Grind off the coating on the repair part of the blade 100 to be repaired, fix the blade 100 to be repaired on the workbench 1, and adjust the position of the print head 3 so that an initial distance is maintained between the coil 5 and the blade 100 to be repaired;

[0057] Move the connecting member 7 to adjust the position of the coil 5, and the initial distance between the coil 5 and the blade 100 to be repaired can be adjusted to 2.5 mm;

[0058] Step S2: Configure the print head 3 with the optimal laser processing process parameters, and configure the alternating current input head 4 with the optimal alternating frequency and alternating input power;

[0059] Step S3: Emit laser and spray metal powder onto the blade 100 to be repaired through the print head 3, and the coil 5 performs induction heating on the repair part of the blade 100 to be repaired;

[0060] Step S4: Through the synchronous movement of the coil 5 and the print head 3, the metal powder is gradually deposited on the repair part of the blade 100 to be repaired.

[0061] In some embodiments, in step S2, the configuration of the print head 3 with the optimal laser processing process parameters and the configuration of the alternating current input head 4 with the optimal alternating frequency and alternating input power specifically include:

[0062] Determine the optimal laser processing parameters according to the orthogonal experiment. The laser processing parameters include laser power, scanning speed, and powder feeding speed. The laser power can be selected from 600 to 1200 W, the scanning speed can be 60 to 150 mm / min, and the powder feeding speed can be 0.3 to 0.6 L / min. Appropriate laser power, scanning speed, and powder feeding speed can achieve the deposition of a single-wall sample with a thickness similar to that of the blade thin wall. The sample surface has fewer defects and a thin wall sample with fewer large-angle grain boundaries.

[0063] Adopt the above optimal laser processing parameters, configure the alternating frequency and alternating input power of the alternating current input head 4, and select the optimal alternating frequency and alternating input power through orthogonal experiments. The alternating frequency is 10 to 20 kHz, and the alternating input power is 2 to 10 kW. The judgment basis for selecting the optimal alternating frequency and alternating input power is that no cracks are formed in the repair area of the blade 100 to be repaired, and the directional continuous growth of the grain structure is the best.

[0064] Complete the blade repair based on the optimal blade laser process parameters, the optimal alternating frequency, and the alternating input power, and realize the disk-type synchronous induction thermomagnetic-assisted laser remanufacturing and tissue performance regulation of the aero-engine blade. In the repair area of the aero-engine blade, refined γ'-strengthening phases are formed, and a dislocation network is established around them, which will help improve the mechanical properties of the blade repair area.

[0065] The following content explains the orthogonal experiment for selecting the optimal alternating frequency and alternating input power. Taking an alternating frequency of 10 kHz and an alternating input power of 2 kW as an example:

[0066] First, turn on the power of the print head 3 and the alternating power supply 8, set an alternating frequency of 10 kHz and an alternating input power of 2 kW on the alternating power supply 8, and then perform induction heating on the blade 100 to be repaired until a stable temperature is reached. Next, combine the optimal blade laser process parameters, the optimal alternating frequency, and the alternating input power to perform synchronous induction thermomagnetic-assisted laser remanufacturing on the blade 100 to be repaired. During this process, the coil 5 and the print head 3 maintain the same movement path. Under the combined action of the laser heat source and the induction heat source, the powder melts on the blade 100 to be repaired to form a molten pool. The molten pool undergoes electromagnetic stirring under the action of the induction magnetic field and gradually cools and solidifies during the movement of the coil 5 and the print head 3. It should be emphasized that the induction heat source provided by the coil 5 not only increases the temperature of the molten pool but also preheats the area to be deposited and cools the deposited area slowly. When the remanufacturing process of the blade 100 to be repaired is completed, the coil 5 and the print head 3 will automatically stop moving, and the powder feeding and laser will also be automatically turned off. At this time, the alternating power supply 8 needs to be turned off, and the blade 100 to be repaired can be taken out only after it has completely cooled.

[0067] Refer to Figure 3, compared with the laser remanufacturing samples without synchronous induction thermomagnetic assistance, the laser remanufacturing samples with synchronous induction thermomagnetic assistance using 2 kW and 4 kW alternating input powers show an inhibitory effect on cracks. Among them, the crack inhibition effect brought by the 4 kW alternating input power is better than that of the 2 kW alternating input power.

[0068] Refer to Figure 4 , compared with the laser remanufacturing samples without synchronous induction thermomagnetic assistance, the laser remanufacturing samples with synchronous induction thermomagnetic assistance using 2 kW and 4 kW alternating input powers show a promotion of the directional continuous growth of the grain structure. Among them, the performance of the directional continuous growth of the grain structure brought by the 4 kW alternating input power is better than that of the 2 kW alternating input power.

[0069] Refer to Figure 5 , compared with the laser remanufacturing samples without synchronous induction thermomagnetic assistance, the laser remanufacturing samples with synchronous induction thermomagnetic assistance using 2 kW and 4 kW alternating input powers show a refinement of the γ′ strengthening phase. Among them, the refinement effect of the γ′ strengthening phase brought by the 4 kW alternating input power is better than that of the 2 kW alternating input power.

[0070] Refer to Figure 6 , synchronous induction thermomagnetic-assisted laser remanufacturing brings a dislocation network around the γ′ strengthening phase.

[0071] The above is only the preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A synchronous induction thermomagnetic assisted laser remanufacturing device for aeroengine blades, characterized in that It includes a workbench, a slide rail, a print head, an alternating current input head and a coil, where: The workbench is used to install and fix the blade to be repaired; The slide rail is fixedly connected to the print head; The print head can move in multiple degrees of freedom and is located above the workbench, and is used to emit laser and spray metal powder onto the blade to be repaired; The coil is a disc-shaped coil, the coil is installed on the alternating current input head and is electrically connected to it, and an avoidance area allowing the laser and metal powder to pass through is provided inside the coil, and the coil is used to inductively heat the repair part of the blade to be repaired; The alternating current input head is slidably installed on the slide rail and can be fixed to the slide rail at a specified position to adjust the distance between the coil and the print head.

2. The aero-engine blade synchronous induction thermomagnetic-assisted laser remanufacturing device according to claim 1, wherein It further includes a connecting piece, the connecting piece is fixedly connected to the slide rail and the print head respectively, and the connecting piece can move in multiple degrees of freedom.

3. The synchronous induction thermomagnetic assisted laser remanufacturing device for aeroengine blades according to claim 1, characterized in that, The coil includes a disc body, a first conductive rod and a second conductive rod; one end of the disc body close to the central axis is connected to the first conductive rod, and the end of the disc body far from the central axis is connected to the second conductive rod; both the first conductive rod and the second conductive rod are connected to the alternating current input head.

4. The aero-engine blade synchronous induction thermomagnetic assisted laser remanufacturing device according to claim 3, characterized in that The disc body is formed by connecting the multi-turn disc coils end to end.

5. The aero-engine blade synchronous induction thermomagnetic assisted laser remanufacturing device according to claim 1, wherein It further includes an alternating current power supply and a wire, and the wire is respectively connected to the alternating current power supply and the alternating current input head.

6. The aero-engine blade synchronous induction thermomagnetic assisted laser remanufacturing device according to claim 1, characterized in that, Under the combined action of laser heating and induction heating, the powder melts on the blade to be repaired to form a molten pool, and the coil is also used to inductively heat the molten pool to control the temperature gradient and solidification rate of the molten pool.

7. A method for synchronous induction thermomagnetic assisted laser remanufacturing of aeroengine blades, which uses the aeroengine blade synchronous induction thermomagnetic assisted laser remanufacturing device described in any one of claims 1-6, and is characterized in that, It includes: Grind off the coating on the repair part of the blade to be repaired, fix the blade to be repaired on the workbench, and adjust the position of the print head so that the initial distance is maintained between the coil and the blade to be repaired; Configure the print head with the best laser processing process parameters, and configure the alternating current input head with the optimal alternating frequency and alternating input power; Emit laser and spray metal powder onto the blade to be repaired through the print head, and the coil inductively heats the repair part of the blade to be repaired; Through the synchronous movement of the coil and the print head, the metal powder is gradually deposited on the repair part of the blade to be repaired.

8. The method for synchronous induction thermomagnetic assisted laser remanufacturing of aeroengine blades according to claim 7, characterized in that, The configuring the print head with the best laser processing process parameters and configuring the alternating current input head with the optimal alternating frequency and alternating input power includes: Determine the best laser processing process parameters according to the orthogonal test, and the laser processing process parameters include laser power, scanning speed and powder feeding speed; Adopt the above best laser processing process parameters to configure the alternating frequency and alternating input power of the alternating current input head, and select the optimal alternating frequency and alternating input power through the orthogonal experiment.

9. The method for synchronous induction thermomagnetic assisted laser remanufacturing of aero-engine blades according to claim 8, characterized in that The laser power is 600 - 1200W, the scanning speed is 60 - 150mm / min, and the powder feeding speed is 0.3 - 0.6L / min.

10. The method for synchronous induction thermomagnetic assisted laser remanufacturing of aeroengine blades according to claim 9, wherein, The alternating frequency is 10 - 20kHz, and the alternating input power is 2 - 10kW.

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