CN111621779A - Laser composite processing method for repairing gradient material of inner wall of aircraft landing gear - Google Patents
Laser composite processing method for repairing gradient material of inner wall of aircraft landing gear Download PDFInfo
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Abstract
The invention discloses a laser composite processing method for repairing a gradient material of an inner wall of an aircraft landing gear, belongs to the field of laser surface modification research, and has the innovation point that the inner wall of the landing gear is repaired by adopting a composite processing mode of a gradient functional material and laser phase change hardening. The forming thickness of the first layer of raw material is 0.4-0.6 mm, so that component transition is realized, and heat damage to a base body is reduced; the alloy coating with the thickness of 1.3-1.6 mm is prepared on the second layer in the same way, the hardness of the coating is lower than that of the first layer, and after mechanical processing, laser phase change hardening treatment is carried out immediately, so that the hardness is obviously improved. The invention not only facilitates the machining process, but also realizes the functional gradient of the repair area, reduces the heat damage to the matrix, and finally forms an alloy coating which has no obvious defect, good metallurgical bonding, wear resistance and corrosion resistance in the repair area of the inner wall of the undercarriage.
Description
Technical Field
The invention relates to a preparation method of a gradient composite material, in particular to a process method for preparing a wear-resistant corrosion-resistant coating with good metallurgical bonding for an area to be repaired of ultrahigh-strength steel such as an inner wall of an undercarriage.
Background
The landing gear is the most important part in the lifting process of the airplane, the structure and the performance of the landing gear greatly influence the use and the safety of the airplane, so the design and the selection of the landing gear not only need to meet the requirements of high specific strength and specific rigidity, but also need to be small enough in size. The steel has the characteristics of high strength, good fatigue property, wear resistance, low crack propagation rate, good processing property and the like, and meanwhile, steel parts are small in size and relatively stable, so that the steel is always used as a main material for designing and manufacturing the landing gear. In order to meet the development needs of aerospace technology in recent 30 years, an ultrahigh-strength steel with yield strength of more than 1350MPa appears in the field of manufacturing industry, is mainly characterized by high strength and good toughness, and is widely applied to key structural components of aircraft landing gears, rocket engine shells, novel missile bodies and the like, such as Aeromet 100, 300M, AF1410, 30CrMnSiNi2A, 18Cr2Ni4WA and the like. However, due to the characteristics of high strength and high hardness, the chips are not easy to bend and break, and generate large cutting force and cutting heat in the machining process, which can seriously affect the quality of the machined surface and the service performance of the cutter, so the material belongs to the material difficult to machine in aviation.
The method is the most direct and effective method for solving the problem of repairing troubles of the landing gear of the airplane and the most economical method for strengthening the inner wall of the landing gear.
The laser deposition technology is a novel surface modification technology, has the remarkable characteristics of rapid solidification and rapid cooling, and can improve the performances of wear resistance, corrosion resistance, oxidation resistance and the like of the metal surface. The technology is suitable for wide material systems, low in dilution rate, small in thermal deformation, good in metallurgical bonding between the substrate and the coating, capable of preparing the coating without obvious defects, more importantly capable of realizing automation, capable of reducing manpower and material resources and saving cost.
The ultra-high strength steel is used as a main manufacturing material of the aircraft landing gear, and has high requirements on local and surface properties besides the overall properties of the material. The cooling speed of the laser phase change hardening treatment is high, the obtained tissue is much finer than that of the tissue treated by the traditional method, the plasticity and the toughness of the core part can be maintained, and the hardness and the wear resistance of the surface can be improved. The treatment method plays a key role in repairing the inner wall of the landing gear.
[ summary of the invention ]
The invention aims to provide a novel gradient composite material and a preparation method thereof aiming at repairing and strengthening the inner wall of an aircraft landing gear, so as to improve the wear resistance, corrosion resistance and oxidation resistance of the inner wall of the landing gear.
The invention relates to a novel gradient composite material for repairing and strengthening an aircraft landing gear, wherein the first layer of transition material comprises the following components in percentage by weight: 0.35-0.55C, 2.95-4.45 Cr, 1.95-3.30 Ni, 0.72-0.85 Mn, 1.60-1.85 Si, 0.08-0.95V, 0.75-1.45 Mo, 0.10-0.40 Cu, and the balance of iron; the second layer of reinforcing material comprises the following components: 0.65-0.85C, 0.53-0.88 Si, 11.05-14.30 Co, 3.20-4.60 Cr, 12.30-14.20 Ni, 0.02-0.06 Mn, 1.30-2.20 Mo, 0.25-0.38 Ti, 0.12-0.35 Al, 0.01-0.02N, and the balance of Fe. Preparing a coating in an area to be repaired on the inner wall of the undercarriage by adopting a laser deposition technology, wherein as shown in figure 1, an alloy transition coating with the thickness of 0.4-0.6 mm is prepared on the first layer, the technological parameters are that the laser power is 1000-1300W, the scanning speed is 4-6 mm/s, the powder feeding speed is 15-23 g/min, the spot diameter is 1.0-2.0 mm, the lap joint rate is 30-50%, the included angle between a laser beam and the normal direction of the inner wall is 10-15 degrees, and the flow of argon protective gas is 15-25L/min; the alloy strengthening coating with the thickness of 1.3-1.6 mm is prepared on the second layer, the technological parameters are 1300-2000W of laser power, 4-7 mm/s of scanning speed, 20-28 g/min of powder feeding speed, 1.0-2.0 mm of spot diameter and 30-50% of lap joint rate, and other parameters are the same as those of the first layer.
After the second layer is deposited and mechanically processed, laser phase change hardening treatment is carried out on the flat surface, the technological parameters are that laser power is 2000-3000W, the diameter of a light spot is 2.0-3.0 mm, scanning speed is 17-50 mm/s, and the included angle between a laser beam and the normal direction of the inner wall is 10-15 degrees.
The method is mainly used for repairing and strengthening the inner wall of the landing gear of the airplane, and the composite coating with good wear resistance, corrosion resistance and oxidation resistance is prepared in the area to be repaired.
Drawings
FIG. 1 is a schematic view of inner bore cladding
FIG. 2 is an interface morphology of a laser deposited gradient coating
FIG. 3 is a graph of the morphology of the tissue after laser phase change hardening treatment
FIG. 4a is a photomicrograph of the specimen prior to frictional wear; FIG. 4b is a photomicrograph of the sample after frictional wear
FIG. 5 is a graph of the hardness contrast profile of a laser deposited gradient coating with a substrate
FIG. 6 is a graph showing the loss in abrasion of a laser deposited gradient coating versus a substrate
Detailed Description
Example 1
The method comprises the following steps:
(1) the first layer of transition material is designed as follows according to mass percentage: c: 0.40 wt%; cr: 3.15
wt％；Ni：2.10wt％；Mn：0.75wt％；Si：1.65wt％；V：0.35wt％；Mo：0.95wt％,
Cu: 0.20 wt%; the balance being iron. The second layer of reinforcing material comprises the following components: c: 0.65 wt%; si: 0.62 wt%;
co: 11.45 wt%; cr: 3.45 wt%; ni: 12.78 wt%; mn: 0.03 wt%; mo: 1.35 wt%; ti: 0.28 wt%; al: 0.18 wt%; n: 0.01 wt%; the balance being iron. Weighing the single element powder in the proportion according to the mass percentage of the components, mixing the powder in a ball mill for 2 hours to obtain uniform powder;
(2) drying the powder in a drying box for 2.5 hours at the drying temperature of 100 ℃; then, respectively filling the powder into two powder conveying barrels for later use;
(3) cleaning and wiping a to-be-repaired area of the inner wall of the aeromet 100 undercarriage by using acetone to remove oil stains and impurities on the surface; then fixing the undercarriage on a positioner, moving the inner hole cladding head of the semiconductor laser to the inner wall repairing area, and focusing (the distance between the cladding head and the section of the area to be repaired is 12 mm);
(4) connecting a powder feeding barrel filled with a transition layer material with a powder feeding port of a laser, setting a program, wherein the technological parameters are that the laser power is 1000W, the scanning speed is 4mm/s, the powder feeding speed is 16g/min, the diameter of a light spot is 1mm, the lap joint rate is 30%, the included angle between a laser head of a used semiconductor laser and the vertical direction is 10 degrees, the operation is carried out under the protection of argon, and the flow of protective gas is 18L/min. After the deposition is finished, cleaning impurities on the lower surface by using a steel brush, wherein the thickness of the finally obtained alloy coating is 0.4 mm;
(5) cleaning powder of a powder feeding pipeline by using argon, replacing a powder feeding barrel, then carrying out a second layer of laser deposition experiment, setting the process parameters to be laser power 1400W, scanning speed 4mm/s, powder feeding speed 23g/min, spot diameter 1.5mm, lap joint rate 30%, setting the same program of other parameters as the first layer, cleaning impurities on the lower surface by using a steel brush after deposition is finished, and finally obtaining the thickness of the alloy coating of 1.4 mm;
(6) taking down the undercarriage from the positioner, machining by using a lathe, monitoring the change condition of cutting force in the machining process in real time by using a three-way dynamometer system, and finally machining a gradient alloy coating with good surface quality and reasonable size, as shown in fig. 2;
(7) and (3) reinstalling the landing gear which is machined on a positioner, and preparing for laser phase change hardening treatment, wherein the process parameters are 2400W of laser power, 2.0mm of spot diameter, 20mm/s of scanning speed and 10 degrees of included angle between the laser beam and the normal direction of the inner wall as shown in figure 3. And simultaneously, the temperature field change is monitored in real time by using temperature detection equipment.
The alloy coatings obtained in this example were subjected to various performance tests.
1. Electrochemical experiments
The composite coating is subjected to polarization curve test by using a CHI660D electrochemical workstation, the test is carried out at room temperature, the electrolyte is a NaCl solution with the mass percentage concentration of 3.5%, the pH value is 6.5, and a three-electrode system is adopted: the sample is a working electrode, the platinum sheet is an auxiliary electrode, the Saturated Calomel Electrode (SCE) is a reference electrode, the potential scanning range is-800 mV, the scanning speed is 20mV/s, and the result shows that the corrosion resistance of the gradient coating is better than that of the raw material.
2. Microhardness
And (3) performing a hardness test by using an HV-1000 type microhardness tester, wherein the load is 50g, the loading time is 10s, performing a multipoint test on the gradient composite coating and the surface of the substrate, and calculating the average value, wherein the average hardness value of the surface of the first transition layer is HRC57.04, the average hardness value of the surface of the second strengthening layer is HRC60.60, the average value of the overall hardness of the gradient coating is HRC58.95, the average hardness value of the surface of the substrate is HRC55.90, and the hardness of the repaired inner wall of the landing gear is improved by 5.46 percent compared with that.
3. Frictional wear performance test
The gradient coating is subjected to a sliding dry friction and wear test on an MMG-10 type friction and wear tester, an upper sample is an annular opposite grinding piece, the material is annealed GCr15 steel, the size is 28mm of outer diameter, 22mm of inner diameter and 12mm of height, a lower sample is a prepared sample to be tested, the size is 43mm of diameter and 4mm of thickness (including the thickness of the obtained gradient coating), as shown in figure 4, the wear surface is an alloy coating, and the surface of the coating is polished to be flat by 2000# abrasive paper. The experimental temperature is room temperature, the rotating speed is 100r/min, the loading force is 100N, the running time is 1h, the abrasion weight loss of the coating is measured to be 1.7mg, and the abrasion weight loss of the substrate material sample is measured to be 3.1mg, and the result shows that the prepared gradient coating has better abrasion resistance.
Example 2
The method comprises the following steps:
(1) the first layer of transition material is designed as follows according to mass percentage: c: 0.50 wt%; cr: 3.85
wt％；Ni：2.60wt％；Mn：0.80wt％；Si：1.75wt％；V：0.65wt％；Mo：1.05wt％,
Cu: 0.28 wt%; the balance being iron. The second layer of reinforcing material comprises the following components: c: 0.75 wt%; si: 0.75 wt%;
co: 12.25 wt%; cr: 3.95 wt%; ni: 13.28 wt%; mn: 0.045 wt%; mo: 1.75 wt%; ti: 0.31 wt%; al: 0.26 wt%; n: 0.02 wt%; the balance being iron. Weighing the single element powder in the proportion according to the mass percentage of the components, mixing the powder in a ball mill for 2.5 hours to obtain uniform powder;
(2) drying the powder in a drying box for 3 hours at the drying temperature of 100 ℃; then, respectively filling the powder into two powder conveying barrels for later use;
(3) cleaning and wiping a to-be-repaired area of the inner wall of the 300M undercarriage by using acetone to remove oil stains and impurities on the surface; then fixing the undercarriage on a positioner, moving the inner hole cladding head of the semiconductor laser to the inner wall repairing area, and focusing (the distance between the cladding head and the section of the area to be repaired is 12 mm);
(5) the following steps except the process parameters: the technological parameters of the first layer transition deposition experiment are that the laser power is 1200W, the scanning speed is 5mm/s, the powder feeding rate is 18g/min, the spot diameter is 1.5mm, the lap joint rate is 40%, the included angle between the laser head of the used semiconductor laser and the vertical direction is 12 degrees, the transition deposition experiment is carried out under the protection of argon, and the flow of the protective gas is 20L/min. After the deposition is finished, cleaning impurities on the lower surface by using a steel brush, wherein the thickness of the finally obtained alloy coating is 0.5 mm; the technological parameters of the second layer reinforced deposition experiment are laser power 1600W, scanning speed 5mm/s, powder feeding speed 25g/min, spot diameter 1.8mm and lapping rate 40%, other parameters are the same as those of the first layer, the procedure is set, after deposition is finished, a steel brush is used for cleaning impurities on the lower surface, and the thickness of the finally obtained alloy coating is 1.45 mm;
the technological parameters of the laser phase change hardening treatment are 2800W of laser power, 3.0mm of spot diameter, 35mm/s of scanning speed and 15 degrees of included angle between the laser beam and the normal direction of the inner wall. The experimental procedure was as in example 1.
The alloy coatings obtained in this example were subjected to various performance tests.
1. Electrochemical experiments
The results of the experimental method and example 1 show that the corrosion resistance of the gradient coating is better than that of the raw material.
2. Microhardness
The experimental method is the same as that of example 1, the average hardness value of the surface of the first transition layer is HRC58.89, the average hardness value of the surface of the second strengthening layer is HRC63.23, the average value of the overall hardness of the gradient coating is HRC61.23, the average hardness value of the surface of the matrix is HRC57.08, and the hardness of the repaired inner wall of the landing gear is improved by 7.3% compared with that of the original material.
3. Frictional wear performance test
The experimental method is the same as that of example 1, the abrasion weight loss of the coating is measured to be 1.58mg, and the abrasion weight loss of the substrate material sample is measured to be 3.2mg, so that the result shows that the prepared gradient coating has better abrasion resistance.
Example 3
The method comprises the following steps:
(1) the first layer of transition material is designed as follows according to mass percentage: c: 0.52 wt%; cr: 4.15
wt％；Ni：3.10wt％；Mn：0.85wt％；Si：1.85wt％；V：0.85wt％；Mo：1.35wt％,
Cu: 0.38 wt%; the balance being iron. The second layer of reinforcing material comprises the following components: c: 0.85 wt%; si: 0.80 wt%;
co: 13.15 wt%; cr: 4.35 wt%; ni: 13.78 wt%; mn: 0.05 wt%; mo: 2.0 wt%; ti: 0.37 wt%; al: 0.32 wt%; n: 0.02 wt%; the balance being iron. Weighing the single element powder in the proportion according to the mass percentage of the components, mixing the powder in a ball mill for 3 hours to obtain uniform powder;
drying the powder in a drying box for 3 hours at the drying temperature of 100 ℃; then, respectively filling the powder into two powder conveying barrels for later use;
(4) cleaning and wiping a to-be-repaired area of the inner wall of the 30CrMnSiNi2A undercarriage by using acetone to remove oil stains and impurities on the surface; then fixing the undercarriage on a positioner, moving the inner hole cladding head of the semiconductor laser to the inner wall repairing area, and focusing (the distance between the cladding head and the section of the area to be repaired is 12 mm);
(5) the method comprises the following steps of except process parameters, wherein the process parameters of a first transition layer deposition experiment are 1300W of laser power, 6mm/s of scanning speed, 20g/min of powder feeding rate, 2mm of spot diameter and 50% of lap joint rate, an included angle between a laser head of a semiconductor laser and the vertical direction is 15 degrees, the process is carried out under the protection of argon, and the flow of protective gas is 25L/min. After the deposition is finished, cleaning impurities on the lower surface by using a steel brush, wherein the thickness of the finally obtained alloy coating is 0.6 mm; the technological parameters of the second layer reinforced deposition experiment are laser power 1800W, scanning speed 7mm/s, powder feeding speed 28g/min, spot diameter 2.0mm and lap joint rate 50%, other parameters are the same as those of the first layer, the procedure is set, after deposition is finished, impurities on the lower surface are cleaned by a steel brush, and the thickness of the finally obtained alloy coating is 1.6 mm;
the technological parameters of the laser phase change hardening treatment are that the laser power is 3000W, the diameter of a light spot is 3.0mm, the scanning speed is 45mm/s, and the included angle between a laser beam and the normal direction of the inner wall is 15 degrees. The experimental procedure was as in example 1.
The alloy coatings obtained in this example were subjected to various performance tests.
1. Electrochemical experiments
The results of the experimental method and example 1 show that the corrosion resistance of the gradient coating is better than that of the raw material.
2. Microhardness
The experimental method is the same as that of example 1, the average hardness value of the surface of the first transition layer is HRC57.79, the average hardness value of the surface of the second strengthening layer is HRC61.16, the average value of the overall hardness of the gradient coating is HRC59.69, the average hardness value of the surface of the matrix is HRC56.72, and the hardness of the repaired inner wall of the landing gear is improved by 5.2% compared with that of the original material.
3. Frictional wear performance test
The experimental method is the same as that of example 1, the abrasion weight loss of the coating is measured to be 1.8mg, and the abrasion weight loss of the substrate material sample is measured to be 3.34mg, so that the result shows that the prepared gradient coating has better abrasion resistance.
Claims (1)
1. A laser composite processing method for repairing a gradient material of an inner wall of an aircraft landing gear is characterized in that a first layer of transition material comprises the following components in percentage by weight: 0.35-0.55C, 2.95-4.45 Cr, 1.95-3.30 Ni, 0.72-0.85 Mn, 1.60-1.85 Si, 0.08-0.95V, 0.75-1.45 Mo, 0.10-0.40 Cu, and the balance of iron; the second layer of reinforcing material comprises the following components: 0.65-0.85C, 0.53-0.88 Si, 11.05-14.30 Co, 3.20-4.60 Cr, 12.30-14.20 Ni, 0.02-0.06 Mn, 1.30-2.20 Mo, 0.25-0.38 Ti, 0.12-0.35 Al, 0.01-0.02N, and the balance of iron;
the inner hole deposition laser composite strengthening method comprises the following steps:
(a) in the area to be repaired of the inner wall of the undercarriage, a gradient coating is prepared by synchronous powder feeding laser deposition, and the first layer of process parameters are as follows: the laser power is 1000-1300W, the scanning speed is 4-6 mm/s, the powder feeding speed is 15-23 g/min, the diameter of a light spot is 1.0-2.0 mm, the overlapping rate is 30-50%, the included angle between a laser beam and the normal direction of the inner wall is 10-15 degrees, the flow of argon protective gas is 15-25L/min, and an alloy transition coating with the thickness of 0.4-0.6 mm is prepared; the second layer process parameters are as follows: the laser power is 1300-2000W, the scanning speed is 4-7 mm/s, the powder feeding speed is 20-28 g/min, the diameter of a light spot is 1.0-2.0 mm, the lap joint rate is 30-50%, and an alloy coating with the thickness of 1.3-1.6 mm is prepared;
(b) after the second layer is deposited and mechanically processed, laser phase change hardening treatment is carried out on the flat surface, the technological parameters are that laser power is 2000-3000W, the diameter of a light spot is 2.0-3.0 mm, scanning speed is 17-50 mm/s, and the included angle between a laser beam and the normal direction of the inner wall is 10-15 degrees.
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