CN113941824A - Device and method for repairing structure and function of piston rod of undercarriage in integrated manner - Google Patents
Device and method for repairing structure and function of piston rod of undercarriage in integrated manner Download PDFInfo
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- CN113941824A CN113941824A CN202111389489.2A CN202111389489A CN113941824A CN 113941824 A CN113941824 A CN 113941824A CN 202111389489 A CN202111389489 A CN 202111389489A CN 113941824 A CN113941824 A CN 113941824A
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Abstract
The invention relates to a device and a method for performing structural and functional integrated repair on cracks of a piston rod of an aircraft landing gear by using a dual-wire variable-polarity plasma arc in a vacuum environment, belonging to the technical field of aerospace equipment remanufacturing. The two different welding wires are used to respectively repair defects and improve the surface corrosion resistance, so that the purpose of integrally repairing the structure and the function is achieved. The multifunctional switching device is designed in the device, the twin-wire plasma welding gun, the resistance wire, the infrared thermometer, the corundum grinding wheel and the blowing device are integrated, switching of different functions is carried out by adjusting the small mechanical arm, and space is saved to a great extent. Compared with the traditional manual repair, the structure and function integrated repair device for the piston rod of the aircraft landing gear greatly improves the repair efficiency and precision of defects.
Description
The technical field is as follows:
the invention relates to the technical field of aerospace equipment remanufacturing, in particular to a device and a method for performing structural and functional integrated repair on cracks of a piston rod of an aircraft landing gear by using a twin-wire variable-polarity plasma arc in a vacuum environment.
Background
The landing gear of the airplane is an extremely important component of the airplane in the process of taking off and landing, the airplane needs to be connected with a body and tires, and when the tires fall to the ground, a large impact force is generated on the landing gear at the moment, so that the landing gear can bear the impact load, and the landing gear cannot have any potential safety hazard. The piston rod of the landing gear of the airplane is an important part on the landing gear, the stress corrosion degree of the piston rod of the landing gear is different according to different environments where the airplane is located, and particularly, when the airplane flies in a humid area or on a sea level with high salinity, the influence on the piston rod of the landing gear of the airplane is larger, and the generated cracks are deeper.
At present, the piston rod of the aircraft landing gear is repaired by adopting a traditional manual surfacing welding mode, the repairing mode is not accurate and low in efficiency, and the repairing efficiency and accuracy of the piston rod of the aircraft landing gear are improved by a mechanical repairing means urgently needed in the industry. The variable polarity plasma arc has higher energy density and efficiency, and is suitable for processing precise workpieces.
The traditional repairing idea is that a single material is adopted for repairing, and repairing materials meeting various performance indexes are rare, so that the comprehensive performance of a workpiece is difficult to improve by a repairing technology. The problem of simultaneous repair of the structure and the function can be well solved by using the variable-polarity plasma arc as a heat source to increase materials of two different welding wires at the defect position.
Therefore, the invention is urgently needed to provide a device and a method for repairing the structure and function of the piston rod of the aircraft landing gear in an integrated manner so as to solve the problems.
Disclosure of Invention
The invention aims to provide a device and a method for integrally repairing the structure and the function of a piston rod of an aircraft landing gear, so that the structure and the function of the inner part and the outer part of the defect of the piston rod of the aircraft landing gear are different, and the aim of integrally repairing the structure and the function is fulfilled.
In order to achieve the purpose, the invention adopts the following technical scheme:
a structural function integrated restoration device for an aircraft landing gear piston rod is characterized by comprising a piston rod body;
the plasma welding gun comprises a plasma welding gun body, a plasma welding gun body and a welding gun body, wherein the plasma welding gun body is used for emitting polarity-changing plasma arcs to sequentially melt different kinds of wires into defects, so that the structures and functions of the inner part and the outer part of the defects are different, and the purpose of integrally repairing the structures and the functions is achieved;
the multifunctional switching device is characterized in that the twin-wire plasma welding gun is arranged at the lowest part of the multifunctional switching device for additive repair, a resistance wire, an infrared thermometer, a corundum grinding wheel and a blowing device are arranged on a small mechanical arm of the multifunctional switching device, and different functions are switched by adjusting the small mechanical arm;
the fixed fixture is used for installing the aircraft landing gear piston rod through the adjustment of the vertical position and the left-right position, and the material increase repair of the defects at different positions is completed by matching the twin-wire plasma welding gun in a rotating mode;
the cathode support rod is used as an auxiliary device for fixing the piston rod of the aircraft landing gear, and plays a role in preventing the piston rod of the aircraft landing gear from falling off and connecting a cathode in the repair process;
vacuum chamber and vacuum pump will twin-wire plasma welding torch, multi-functional auto-change over device, fixed fixture, negative pole bracing piece, defect detector and guide rail are all integrated and are in vacuum chamber internal work, the vacuum pump carries out evacuation processing with the vacuum chamber, prevents to take place oxidation reaction at vibration material disk repair in-process, prevents simultaneously that the dropping liquid from splashing protection workman safety.
The control cabinet, the computer, the air pump, the air guide pipe, the polarity-changing plasma welding machine and the wire feeder are all arranged outside the vacuum box.
Optionally, the multifunctional switching device is fixed on a guide rail at the top in the vacuum box and can slide left and right, the twin-wire plasma welding gun moves along with the multifunctional switching device, and the two wire feeders are respectively used for connecting a welding wire with the twin-wire plasma welding gun through the outside of the vacuum box. The bottom of small-size arm is fixed, and multi-angle is adjusted to mid-mounting axle type part, can switch the instrument through extending and contracting small-size arm according to the operation requirement of difference, can fold to pack up to the instrument that does not use and save space.
Optionally, the method comprises the steps of:
(1) detecting defects, namely detecting the defects of the clamped undercarriage piston rod by adjusting the defect detector on the guide rail, and detecting the shape, position and depth of the defects;
(2) defect polishing, namely switching a multifunctional switching device to the corundum grinding wheel to polish the defect, and removing falling powder by using the blowing device;
(3) repairing the structure, namely aligning a plasma welding gun on the multifunctional switching device to the defect position, and performing additive repair by using a 300M steel welding wire;
(4) performing function repair, namely aligning a plasma welding gun on the multifunctional switching device to the defect, and cladding the defect by using a TC4 titanium alloy welding wire;
(5) fine trimming, namely switching the multifunctional switching device to the corundum grinding wheel, grinding the part after material increase, removing redundant material increase tissues and ensuring that the dimensional precision meets the assembly requirement;
(6) local heat treatment, namely switching the multifunctional switching device to the resistance wire and an infrared thermometer, using the resistance wire to align with the defect to carry out local stress relief annealing treatment, and monitoring the temperature by the infrared thermometer;
optionally, in step 3, the high-frequency pulse frequency of the variable polarity plasma welding machine is 1000Hz, the low-frequency pulse frequency is 5Hz, the power frequency is 40Hz, the plasma current is 110A, the arc voltage is 20V, the arc height is 6mm, the diameter of the welding wire is 0.8mm, the material increase speed is 1.2m/min, the wire feeding speed is 1.5m/min, the arc length is 5mm, and the layer cooling time is 60 s.
Optionally, in the step 4, the polarity-changed plasma welding machine has a high-frequency pulse frequency of 800Hz, a low-frequency pulse frequency of 4Hz, a power frequency of 30Hz, a plasma current of 110A, an arc voltage of 20V, an arc height of 5mm, a wire diameter of 0.8mm, a material increase speed of 2.4m/min, a wire feed speed of 2m/min, and a layer cooling time of 40 s.
Optionally, in the step 6, the annealing temperature is kept between 550 ℃ and 650 ℃, the temperature is kept for 2 hours, the temperature is slowly reduced to 200 ℃, and air cooling is carried out.
The invention has the beneficial effects that:
according to the device and the method for repairing the structure and the function of the piston rod of the aircraft landing gear in an integrated manner, the defects are repaired and the surface corrosion resistance is improved by using two different welding wires, so that the purpose of repairing the structure and the function in an integrated manner is achieved. The double-wire plasma welding gun, the resistance wire, the infrared thermometer, the corundum grinding wheel and the blowing device are arranged on the multifunctional switching device, switching of different functions is carried out by adjusting the small mechanical arm, various tools are integrated together, operation is convenient, and space is saved to the greatest extent. All the operation processes are carried out in the vacuum box, so that the metal oxidation reaction generated in the processing process is prevented, and the safety of a master worker is also protected by preventing the dropping liquid from splashing. All devices are connected with the computer, and compared with the conventional manual repair, the automatic repair is completely realized in the whole repair step, so that the cost is saved, and meanwhile, the repair efficiency and speed are greatly improved.
Drawings
FIG. 1 is a schematic structural diagram of a structurally and functionally integrated repairing device for a piston rod of an aircraft landing gear;
FIG. 2 is a schematic structural diagram of a multifunctional switching device of the device for repairing the structural and functional integration of the piston rod of the landing gear of the aircraft
FIG. 3 is a schematic structural view of a right fixing clamp of the device for repairing the structural and functional integration of the piston rod of the undercarriage according to the invention
FIG. 4 is a schematic structural view of a left fixing clamp of the device for repairing the structural and functional integration of the piston rod of the undercarriage according to the invention
FIG. 5 is a schematic structural diagram of a cathode support rod of the structural-functional integrated repair device for the piston rod of the aircraft landing gear
In the figure:
1-a twin-wire plasma welding gun; 2-a multifunctional switching device; 3-a small mechanical arm; 4-resistance wire; 5-infrared thermometer; 6-corundum grinding wheel; 7-blowing means; 8-fixing the fixture; 9-aircraft landing gear piston rod; 10-a cathode support rod; 11-a vacuum box; 12-a vacuum pump; 13-defect detector; 14-a guide rail; 15-a control cabinet; 16-a computer; 17-an air pump; 18-an airway tube; 19-a variable polarity plasma welder; 20-a wire feeder;
the specific implementation mode is as follows:
the present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.
In the description of the present invention, unless otherwise expressly specified or limited, the terms "connected" and "connected" are to be construed broadly, e.g., as meaning a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description of the present embodiment, the terms "upper", "lower", "right", etc. are used in an orientation or positional relationship based on that shown in the drawings only for convenience of description and simplicity of operation, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used only for descriptive purposes and are not intended to have a special meaning.
The piston rod of the aircraft landing gear plays a role in flight safety, but the problems of low efficiency and low precision can be caused by adopting a manual repair mode for defect repair at present. And the common repairing mode adopts a single material for repairing, so that the workpiece cannot be comprehensively and comprehensively repaired.
In order to solve the above problems, the present embodiment provides a device and a method for repairing the structural function of a piston rod of an aircraft landing gear, which can be used in the technical field of aerospace equipment manufacturing. The embodiment is described by taking the example that the structural and functional integrated repairing device of the piston rod of the aircraft landing gear repairs the defects on the piston rod of the aircraft landing gear.
As shown in figure 1, a defect detector (13), a guide rail (14), a multifunctional switching device (2), a twin-wire plasma welding gun (1), a resistance wire (4), an infrared thermometer (5), a corundum grinding wheel (6), a blowing device (7), a fixing clamp (8) and a cathode supporting rod (10) are arranged in a vacuum box (11). The piston rod (9) of the landing gear of the airplane is fixed on the fixing clamps (8) on the left side and the right side, and the lower part of the piston rod is supported by the cathode support rod (10). Meanwhile, a vacuum pump (12), a control cabinet (15), a computer (16), an air pump (17), an air guide pipe (18), a polarity-changing plasma welding machine (19) and a wire feeder (20) are arranged outside the vacuum box (11).
Guide rails (14) are arranged at the top end and two sides in the vacuum box (11), and the guide rails (14) at the top can move up and down on the guide rails (14) at the two sides to change positions.
The defect detector (13) is arranged on a side guide rail (14) and can move up and down, the rotary fixing clamp (8) is matched to carry out omnibearing scanning on the piston rod of the undercarriage of the airplane, the position, the shape and the depth of a defect are found, scanning data are transmitted into a computer to generate a three-dimensional digital analog, a newly generated model is compared with an original model by using a computer (16), a repairing scheme and a path are automatically planned, and preparation is made for the next repairing work.
As shown in fig. 2, the multifunction switching device (2) is mounted on the head rail (14) so as to be movable in the left-right direction. Install two wire plasma welding torch (1) in multi-functional auto-change over device (2) lower part, can not move alone and can only follow multi-functional auto-change over device (2) and remove jointly, through the up-and-down motion of top guide rail (14) to and the rotatory fixed fixture (8) of cooperation, two wire plasma welding torch (1) can be nimble carry out the vibration material disk to aircraft undercarriage piston rod and restore.
As shown in figure 2, four small mechanical arms (3) are arranged on the multifunctional switching device (2), the lower ends of the small mechanical arms (3) are fixed, shaft parts are arranged in the middle of the small mechanical arms and can be adjusted at multiple angles, and a resistance wire (4), an infrared thermometer (5), a corundum grinding wheel (6) and a blowing device (7) are respectively arranged on the outermost sides of the small mechanical arms (3), so that the functions of polishing and heat treatment can be realized. According to different use requirements, the angle of the small mechanical arm (3) is adjusted, different use tools are switched, and the idle tools can be folded and folded to save redundant space, so that the displacement range of the multifunctional switching device (2) is expanded.
As shown in fig. 3 and 4, two fixing fixtures (8) are respectively installed on the two side rails (14) to be movable up and down. The right clamp is used for fixing the piston rod (9) of the aircraft landing gear in a three-point type internal and external opening and closing mode. The left side fixture can stretch out and draw back from left to right, and the left side fixture contracts earlier before the installation and vacates installation space for undercarriage piston rod (9), waits that the right side fixture accomplishes and fixes for the first time the back left side fixture extends and makes undercarriage piston rod (9) accomplish the secondary fastening.
As shown in fig. 5, the cathode support rod (10) is located at the bottom of the vacuum box (11) and can stretch up and down, when the piston rod (9) of the undercarriage of the airplane is clamped, the cathode support rod (10) is located in the middle of the vacuum box and plays a supporting role for the piston rod (9) of the undercarriage of the airplane, the top of the cathode support rod is of an arc-shaped structure and is matched with the piston rod in shape, and the piston rod (9) of the undercarriage of the airplane is prevented from falling off in the installation and material increase processes. Meanwhile, the contact part of the cathode supporting rod (10) and the piston rod is made of copper and is connected with a variable polarity plasma welding machine (19) through a copper lead to serve as a cathode.
A polarity-variable plasma welding machine (19) is arranged at the lower part of the right side of the vacuum box (11).
An air pump (17) is arranged above the polarity-changing plasma welding machine (19) and is connected with a blowing device (7) on the multifunctional switching device (2) through an air duct (18), and the falling powder can be blown off when the workpiece is polished.
And a wire feeder (20) which is respectively 300M steel and TC4 titanium alloy welding wires is arranged above the air pump (17) and is used for feeding wires to the plasma welding gun (1) when the material adding process is started.
A vacuum pump (12) is arranged on the left side of the vacuum box (11), the vacuum pump (12) is connected with the vacuum box (11), and the vacuum pump (12) is started after a workpiece is fixed to vacuumize the vacuum box (11) so as to prevent the workpiece from being oxidized in the repairing process.
The control cabinet (15) is placed on the left side of the vacuum pump (12), the control cabinet (15) is connected with the vacuum pump (12), the vacuum box (11), the defect detector (13), the multifunctional switching device (2), the twin-wire plasma welding gun (1), the resistance wire (4), the infrared thermometer (5), the corundum grinding wheel (6), the blowing device (7), the fixing fixture (8), the cathode supporting rod (10), the air pump (17), the air guide pipe (18), the polarity-changing plasma welding machine (19), the computer (16) and the wire feeding machine (20) through a wire. An integrated operating system is formed, and the operation of all devices is controlled in a unified mode.
The computer (16) is arranged above the vacuum pump (12) and connected with the control cabinet (15), and the control cabinet (15) is operated to complete the operation of all the devices, so that the whole repair process is automatically carried out.
The specific repairing process is as follows:
(1) defect detection, namely performing defect detection on the clamped undercarriage piston rod (9) by adjusting the defect detector (13) on the guide rail (14) to detect the shape, position and depth of the defect;
(2) defect polishing, namely switching the multifunctional switching device (2) to the corundum grinding wheel (6), polishing the defect part, and removing falling powder by using the blowing device (7);
(3) structural repair, namely aligning a plasma welding gun (1) on the multifunctional switching device (2) to a defect position, and performing additive repair by using a 300M steel welding wire, wherein the material is the same as the base material of the piston rod (9) of the aircraft landing gear, so that structural repair is met;
(4) performing function repair, namely aiming a plasma welding gun on the multifunctional switching device (2) at a defect, cladding the defect by using a TC4 titanium alloy welding wire, and cladding the material serving as the outermost layer on the surface of the defect so as to perform anti-corrosion treatment to prevent the generation of cracks again;
(5) fine trimming, namely switching the multifunctional switching device (2) to the corundum grinding wheel (6), grinding the additive part, removing redundant additive tissues and ensuring that the dimensional precision meets the assembly requirement;
(6) local heat treatment, namely switching the multifunctional switching device (2) to the resistance wire (4) and the infrared thermometer (5), aligning the resistance wire (4) to the defect to perform local stress relief annealing treatment, and monitoring the temperature by the infrared thermometer (5);
in the step 3, the high-frequency pulse frequency of the polarity-changing plasma welding machine (19) is 1000Hz, the low-frequency pulse frequency is 5Hz, the power frequency is 40Hz, the plasma current is 110A, the arc voltage is 20V, the arc height is 6mm, the diameter of a welding wire is 0.8mm, the material increase speed is 1.2m/min, the wire feeding speed is 1.5m/min, the arc length is 5mm, and the layer cooling time is 60 s.
In the step 4, the polarity-changing plasma welding machine (19) is changed, the high-frequency pulse frequency is 800Hz, the low-frequency pulse frequency is 4Hz, the power frequency is 30Hz, the plasma current is 110A, the arc voltage is 20V, the arc height is 5mm, the diameter of the welding wire is 0.8mm, the material adding speed is 2.4m/min, the wire feeding speed is 2m/min, and the layer cooling time is 40 s. In the step 6, the annealing temperature is kept between 550 ℃ and 650 ℃, the temperature is kept for 2 hours, the temperature is slowly reduced to 200 ℃, and air cooling is carried out.
It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and all embodiments are not necessarily or exclusively exhaustive. This summary should not be construed to limit the present invention. Other variations and modifications of the present invention will be apparent to those of ordinary skill in the art in light of the above teachings. It should be understood that any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (6)
1. A structural function integrated restoration device for an aircraft landing gear piston rod is characterized by comprising a piston rod body;
the plasma welding gun comprises a double-wire plasma welding gun (1), wherein polarity-variable plasma arcs emitted by the double-wire plasma welding gun (1) are used for sequentially melting different kinds of wires into defects, so that the structures and functions inside and outside the defects are different, and the purpose of integrally repairing the structures and functions is achieved;
the device comprises a multifunctional switching device (2), wherein the twin-wire plasma welding gun (1) is installed at the lowest part of the multifunctional switching device (2) for additive repair, a resistance wire (4), an infrared thermometer (5), a corundum grinding wheel (6) and a blowing device (7) are installed on a small mechanical arm (3) of the multifunctional switching device (2), and different functions are switched by adjusting the small mechanical arm (3);
the fixed fixture (8) is used for installing the aircraft landing gear piston rod (9) through adjusting the vertical position and the left-right position, and the double-wire plasma welding gun (1) is matched in a rotating mode to complete additive repair of defects at different positions;
the cathode support rod (10) is used as an auxiliary device for fixing the undercarriage piston rod (9), and plays a role in preventing the undercarriage piston rod (9) from falling off and connecting a cathode in a repairing process;
the device comprises a vacuum box (11) and a vacuum pump (12), wherein the twin-wire plasma welding gun (1), the multifunctional switching device (2), the fixing clamp (8), a cathode supporting rod (10), a defect detector (13) and a guide rail (14) are all integrated in the vacuum box (11) to work, the vacuum pump (12) carries out vacuum pumping treatment on the vacuum box (11), oxidation reaction is prevented from occurring in the material increase repairing process, and meanwhile, dropping liquid is prevented from splashing to protect the safety of workers;
the control cabinet (15), the computer (16), the air pump (17), the air guide pipe (18), the polarity-changing plasma welding machine (19) and the wire feeder (20) are all arranged outside the vacuum box (11).
2. The device for repairing the structural and functional integration of the piston rod of the aircraft landing gear according to claim 1 is characterized in that the multifunctional switching device (2) is fixed on a guide rail (14) at the top inside the vacuum box (11) and can slide left and right, the twin-wire plasma welding gun (1) moves along with the multifunctional switching device (2), and the two wire feeders (20) are respectively used for connecting welding wires with the twin-wire plasma welding gun (1) through the outside of the vacuum box (11). The bottom of small-size arm (3) is fixed, and mid-mounting axle type part can carry out multi-angle and adjust, can switch the instrument through extending and contracting small-size arm (3) according to the operation requirement of difference, can fold to pack up to save space to the instrument that does not use.
3. The method for structurally and functionally integrally repairing a piston rod of an aircraft landing gear according to claim 1, comprising the following steps:
(1) defect detection, namely performing defect detection on the clamped undercarriage piston rod (9) by adjusting the defect detector (13) on the guide rail (14) to detect the shape, position and depth of the defect;
(2) defect polishing, namely switching the multifunctional switching device (2) to the corundum grinding wheel (6), polishing the defect part, and removing falling powder by using the blowing device (7);
(3) repairing the structure, namely aligning a double-wire plasma welding gun (1) on the multifunctional switching device (2) to the defect position, and performing additive repair by using a 300M steel welding wire;
(4) performing function repair, namely aligning a double-wire plasma welding gun (1) on the multifunctional switching device (2) to the defect, and cladding the defect by using a TC4 titanium alloy welding wire;
(5) fine trimming, namely switching the multifunctional switching device (2) to the corundum grinding wheel (6), grinding the additive part, removing redundant additive tissues and ensuring that the dimensional precision meets the assembly requirement;
(6) and local heat treatment, namely switching the multifunctional switching device (2) to the resistance wire (4) and the infrared thermometer (5), using the resistance wire (4) to align to the defect to carry out local stress relief annealing treatment, and monitoring the temperature by the infrared thermometer (5).
4. The method for integrally repairing the structure and the function of the piston rod of the aircraft landing gear according to claim 3, wherein in the step 3, a variable polarity plasma welding machine (19) has the high-frequency pulse frequency of 1000Hz, the low-frequency pulse frequency of 5Hz, the power frequency of 40Hz, the plasma current of 110A, the arc voltage of 20V, the arc height of 6mm, the diameter of a welding wire of 0.8mm, the material increase speed of 1.2m/min, the wire feeding speed of 1.5m/min, the arc length of 5mm and the layer cooling time of 60 s.
5. The method for repairing the functional integration of the arc additive structure of the aircraft landing gear piston rod according to the claim 3, wherein in the step 4, a polarity-changing plasma welding machine (19) is adopted, the high-frequency pulse frequency is 800Hz, the low-frequency pulse frequency is 4Hz, the power frequency is 30Hz, the plasma current is 110A, the arc voltage is 20V, the arc height is 5mm, the diameter of a welding wire is 0.8mm, the additive speed is 2.4m/min, the wire feeding speed is 2m/min, and the layer cooling time is 40 s.
6. The method for repairing the functional integration of the electric arc additive structure of the piston rod of the aircraft landing gear according to claim 3, wherein in the step 6, the annealing temperature is kept between 550 ℃ and 650 ℃, the temperature is kept for 2 hours, the temperature is slowly reduced to 200 ℃, and air cooling is carried out.
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| CN114473152A (en) * | 2022-03-03 | 2022-05-13 | 南京理工大学 | Preparation method and device of double-wire-feeding polarity-variable plasma Ni-Nb superalloy |
| CN114473152B (en) * | 2022-03-03 | 2024-04-16 | 南京理工大学 | Preparation method and device of double-wire-feeding polarity-changing plasma Ni-Nb superalloy |
| CN115056943A (en) * | 2022-06-16 | 2022-09-16 | 南京航空航天大学 | Solid-phase additive repair device and method |
| CN115056943B (en) * | 2022-06-16 | 2023-11-14 | 南京航空航天大学 | Solid-phase material-increasing repairing device and method |
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| CN113941824B (en) | 2022-12-30 |
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