CN114438488B - Synergistic repairing method for additive deformation prevention of aircraft generator shell - Google Patents
Synergistic repairing method for additive deformation prevention of aircraft generator shell Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
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- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
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- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/005—Ferrous alloys, e.g. steel alloys containing rare earths, i.e. Sc, Y, Lanthanides
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
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Abstract
The invention relates to the technical field of laser cladding additive repair, in particular to an additive deformation-preventing collaborative repair method for an aircraft generator shell, which comprises the following steps of: designing an anti-deformation device according to the technological parameter-heat dissipation-deformation relation, and carrying out component optimization design on the current repairing powder to prepare repairing powder; removing defects of the part, and polishing and cleaning the area to be repaired; performing magnetic powder flaw detection on the area to be repaired, and protecting the outside of the area to be repaired by using aluminum foil; and fixing the part to be repaired on the deformation preventing device, and spraying the prepared repair powder on the part to be repaired by using laser cladding equipment to repair. The welding seam forming quality is good, and the deformation of a workpiece is small; secondly, the laser cladding is high in laser energy density, small in heat input amount, high in crystallization speed, fine in weld joint crystal grains and good in mechanical property of a welded joint; thirdly, the laser cladding HAZ is small; fourth, repair cycle is greatly reduced, and cycle is greatly shortened.
Description
Technical Field
The invention relates to the technical field of laser cladding additive repair, in particular to an additive deformation-preventing collaborative repair method for an aircraft generator shell.
Background
The 12Cr2Ni4A alloy steel has very high strength and hardness on the surface after carburization quenching tempering, and has very good matching of core strength and toughness and plasticity, so that the steel is widely applied to important thin-wall parts with larger section and higher load on an airplane and requiring good toughness. The main function of a certain model of aircraft 12Cr2Ni4A steel shell is to transmit load, the use frequency is high, the shell is seriously worn due to friction in the use process, welding repair is usually adopted for repair, the shell is thin in wall, the welding is easy to pass through in the repair process, and the normal working performance of the aviation parts cannot be guaranteed. The casings in which this occurs are currently treated in a new way, with high costs and often with blocked repair progress due to the difficulty of supplying spare parts. Therefore, it is necessary to find a synergistic repair process for shell material increase and deformation prevention to achieve the purposes of improving repair quality, saving cost and shortening repair period.
Disclosure of Invention
Aiming at the technical problems, the invention provides an additive anti-deformation cooperative repairing method for an aircraft generator shell. And heating the cladding material and the surface of the matrix at the damaged part of the structural part by using a laser beam by utilizing a laser material-increasing anti-deformation cooperative remanufacturing method, so that the required special material is welded on the damaged surface of the part. The technology has firm metallurgical bonding with the matrix, high bonding strength, ultrahigh heating and cooling speed to refine the crystal grains of the cladding layer, and has the series of advantages of small heat influence, small deformation, strong applicability and the like.
The technical problems to be solved by the invention are realized by adopting the following technical scheme:
an aircraft generator shell material-adding anti-deformation cooperative repairing method comprises the following steps:
firstly, designing an anti-deformation device according to a process parameter-heat dissipation-deformation relation, and carrying out component optimization design on the current repairing powder to prepare repairing powder;
secondly, removing defects of the parts, and polishing and cleaning the area to be repaired;
thirdly, performing magnetic particle inspection detection on the area to be repaired, if the detection is unqualified, reworking to the second step until the detection is qualified, and protecting the outside of the area to be repaired by using aluminum foil;
fourthly, fixing the part to be repaired on an anti-deformation device, setting technological parameters according to the repair requirement, and spraying the repair powder prepared in the first step on the part to be repaired by using laser cladding equipment to repair;
machining the surface of the repaired part, performing magnetic flaw detection after the machining, and detecting whether a crack exists or not, and if so, repeating the steps (two) to (five) until no crack exists;
and (six) carrying out the same repair process by adopting a sample which is the same as the material of the part, and carrying out a mechanical tensile test to verify the mechanical property effect of the part.
Preferably, the deformation preventing device in the step (one) comprises a base (1), a center positioning circular ring (2) arranged at the top of the base (1) and positioning blocks (3) symmetrically distributed on two sides of the center positioning circular ring (2).
Preferably, the deformation preventing means in step (one) is a red copper material.
Preferably, the powder composition after the component optimization design in the step (one) specifically comprises: c:0.25 to 0.28 percent; mn:0.7 to 0.8 percent; cr:0.8 to 0.9 percent; si:0.8 to 0.9 percent; rare earth 0.008% -0.009%; s: less than or equal to 0.03 percent, P: less than or equal to 0.03 percent; fe: the balance.
Preferably, the preparation specific process of the repair powder after the optimization design in the step (one) is as follows: batching, smelting, atomizing, screening powder collection, performance analysis and testing.
Preferably, polishing and cleaning in the step (two) are specifically as follows: cleaning by adopting a steel wire brush or a mechanical polishing tool, removing an oxide layer, leaking out metallic luster, and cleaning by using acetone.
Preferably, the process parameters in step (four) are:
carrier gas: 99.999% high purity argon;
laser power: 500-800W;
scanning speed: 8-10 mm/s;
powder carrying gas: 380-400L/h;
overlap ratio: 50-60%;
spot diameter: 1.5-2.5 mm.
Preferably, in the step (four), after the laser cladding one layer, the surface oxide is cleaned, and after the temperature is cooled to room temperature, the next layer is clad.
Preferably, the machining treatment in step (five) is specifically an electric grinding head or a pneumatic grinding.
The beneficial effects of the invention are as follows:
compared with the traditional argon arc welding repair method, the method has the advantages that firstly, the welding seam forming quality is good, and the deformation of the workpiece is small; secondly, the laser cladding is high in laser energy density, small in heat input amount, high in crystallization speed, fine in weld joint crystal grains and good in mechanical property of a welded joint; thirdly, the laser cladding HAZ is small; fourth, repair cycle is greatly reduced, and cycle is greatly shortened.
Drawings
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
FIG. 1 is a schematic structural view of a generator housing component of an aircraft to be repaired;
FIG. 2 is a schematic structural view of an anti-deformation apparatus according to the present invention;
FIG. 3 is a schematic view of an assembly of a housing assembly and an anti-deformation device;
FIG. 4 is a flow chart of additive anti-deformation cooperative repair in the present invention;
fig. 5 is a schematic structural diagram of a sample.
In the figure: 1. a base; 2. a center positioning circular ring; 3. and (5) positioning blocks.
Detailed Description
In order that the manner in which the invention is attained, as well as the features and advantages thereof, will be readily understood, a more particular description of the invention will be rendered by reference to the appended drawings.
The material of certain aircraft part accessory is 12Cr2Ni4A carburizing steel, and the friction between the aircraft part accessory and a shell component causes serious abrasion in the use process, so that the assembly clearance is affected, the strength of the shell is reduced, and the normal working performance of the aircraft part accessory cannot be ensured. The casings in which this occurs are currently treated in a retrofit manner, with high repair costs and often with blocked repair progress due to the difficulty in supplying spare parts. The invention innovatively uses the laser additive remanufacturing technology to replace the new technology, and adopts the laser beam to heat the cladding material and the surface of the matrix, so that the required special material is welded on the surface of the part, the repair of the damaged part is realized, and the service life of the aircraft shell is prolonged.
As shown in fig. 4, the synergistic repairing method for the additive deformation prevention of the aircraft generator shell comprises the following steps:
firstly, designing an anti-deformation device according to the relation of technological parameters, heat dissipation and deformation, and carrying out component optimization design on the current repairing powder to prepare the repairing powder.
As shown in fig. 1, the part of the aircraft generator housing to be repaired is of a hollow structure, and laser cladding is easy to weld through and undercut, so that a laser material-increasing anti-deformation cooperative repair process must be designed to ensure repair quality.
As shown in fig. 2, the deformation preventing device is composed of a base 1, a center positioning ring 2 arranged on the base 1, and two positioning blocks 3 distributed on two sides of the center positioning ring 2. The outer diameter of the center positioning ring 2 is matched with the hollow inner diameter of the aircraft generator shell part, and the two positioning blocks 2 are matched with the two convex edge structures on the aircraft generator shell part. In order to facilitate heat dissipation, the deformation preventing device is made of red copper material.
The technological parameter-heat dissipation-deformation relation is as follows: the process parameters mainly influence the whole heat accumulation process, and mainly refer to laser power, scanning speed, spot diameter and laser repair interval time, wherein the heat accumulation is large as the cladding interval is shorter each time, and the heat accumulation is larger and the heat expansion deformation is large as the heat expansion and the cold contraction are known; the whole repair process adopts the deformation-preventing tool made of red copper, and the deformation-preventing tool can prevent deformation by positioning and reverse deformation, so that the repair quality is improved.
The existing repair powder is subjected to component optimization design:
the components of the alloy powder for repairing at present are as follows: 0.25 to 0.30 percent, mn:0.7 to 1.0 percent, cr:0.8% -1.0%, si:0.8 to 1.0 percent; the method comprises the steps of carrying out a first treatment on the surface of the S: less than or equal to 0.03 percent, P: less than or equal to 0.03 percent; fe: the balance.
Aiming at the influence of each element on the alloy performance, the composition optimization design of the current 12Cr2Ni4A steel alloy powder is as follows: c:0.25 to 0.30 percent, mn:0.7 to 0.9 percent, cr:0.8 to 0.9 percent, si:0.8 to 0.9 percent; 0.007 to 0.010 percent of rare earth; s: less than or equal to 0.03 percent, P: less than or equal to 0.03 percent; fe: the balance.
And according to the effect of each element on alloy performance, the final components of the repairing powder are optimally designed as follows: c:0.25 to 0.28 percent, mn:0.7 to 0.8 percent, cr:0.8 to 0.9 percent, si:0.8 to 0.9 percent; rare earth 0.008% -0.009%; s: less than or equal to 0.03 percent, P: less than or equal to 0.03 percent; fe: the balance. Wherein the rare earth element is at least one of Se, lu and Yb, and finally, se is preferable.
According to the repair requirement, the prepared powder for repair needs to meet the following conditions:
(a) Has good fluidity of less than or equal to 25S/50g, high sphericity of more than or equal to 0.99 and low oxygen content of less than or equal to 500ppm.
(b) The thermal expansion coefficient of the powder material is (8-9) 10 －6 K －1 The thermal conductivity is (90-120) Wm —1 K －1 The melting point is 1400-1500 ℃ and is as close as possible to the material of the repaired component so as to reduce the residual stress of the alloy layer.
(c) The powder has good wettability, the wettability is related to the surface tension, the smaller the surface tension is, the smaller the wetting angle is, the better the liquid fluidity is, and the wetting angle of the powder in a molten state is less than or equal to 70 degrees.
Preparation of repair powder: comprising the following steps: batching, smelting, atomizing, screening powder collection, performance analysis and testing.
(A) The specific process of the ingredients is as follows: firstly, preparing materials, and preprocessing the prefabricated alloy base material according to the requirement of the preferable alloy powder component, wherein the preprocessing comprises oil removal, rust removal and the like. Analyzing chemical components, gas content and impurity content by taking a sample, and if the chemical component requirement determined in the step (one) is met, carrying out the next step; if the requirements are not met, the raw materials need to be reconfigured until the requirements are met.
(B) The specific smelting process comprises the following steps: adjusting power supply smelting power and smelting frequency, wherein the smelting power is as follows: 35-45KW, smelting frequency: 3-4KHz; smelting the prepared parent metal to obtain alloy solution.
(C) The specific process of atomization is as follows: in the atomization process, the powder quality is controlled by controlling technological parameters such as the atomization temperature, the atomization pressure, the gas flow, the alloy flow and the like, wherein the atomization temperature is 1400-1500 ℃, the atomization pressure is 4-6MPa, the gas flow is 18-25L/min, and the alloy flow is 0.6-1.2L/min. After atomization is completed, the prepared alloy powder is collected in a powder collecting tank through a cyclone, and the powder collecting tank is directly transferred into a glove box in a sealed state.
(D) The specific process of screening powder collection is as follows: sieving with 60 mesh standard sieve, and storing 60 mesh powder in stainless steel container under argon atmosphere to ensure the cleanliness of the powder. And then collecting and sieving the powder, and sieving the powder by adopting a 270-mesh and 100-mesh sieve to obtain the powder with 53-150 mu m section granularity.
(E) The specific process of the performance analysis and test is as follows: and (3) carrying out component analysis, microstructure analysis and performance test (including flowability, apparent density and the like) on the sieved powder to finally obtain the powder meeting the component design requirements.
And secondly, removing defects of the part, cleaning the part within the range of 20mm around the to-be-repaired area of the part by using a wire brush or a mechanical polishing tool, removing an oxide layer, ensuring that the metallic luster is exposed, the surface is clean, and cleaning by using acetone.
And thirdly, performing magnetic particle inspection detection on the area to be repaired, if the detection is unqualified, reworking to the second step until the detection is qualified, and protecting other parts of the part except the repair area, which are possibly irradiated by laser, by using aluminum foil and the like, so as to prevent the substrate of other parts from being damaged by the irradiation of the laser in the repair process.
And fourthly, fixing the part to be repaired on the deformation preventing device, setting technological parameters according to the repair requirement, and spraying the repair powder prepared in the step (one) on the part to be repaired by using laser cladding equipment to repair as shown in fig. 3. In the repairing process, after a layer of the surface oxide is cleaned by laser cladding, and after the temperature is cooled to room temperature, a next layer of the surface oxide is clad.
The process parameters are as follows:
laser cladding equipment: laser cladding complete equipment (2 KWIPG lasers, library card robots, etc.);
carrier gas: 99.999% high purity argon;
laser power: 500-800W;
scanning speed: 8-10 mm/s;
powder carrying gas: 380-400L/h;
overlap ratio: 50-60%;
spot diameter: 1.5-2.5 mm.
And fifthly, carrying out surface processing treatment on the surface of the repaired part by mechanical methods such as an electric grinding head, pneumatic grinding, turning and grinding (grinding), carrying out magnetic flaw detection after the surface processing to detect whether cracks exist, and repeating the steps (two) to (five) until no cracks exist.
And (six) carrying out the same repair process by adopting a sample which is the same as the material of the part, and carrying out a mechanical tensile test to verify the mechanical property effect of the part.
Specifically, a tensile test bar is processed by adopting a 12Cr2Ni4A material which is the same as that of an accessory of an airplane part, a groove notch is prefabricated on the test bar, a sample form is shown in fig. 5, a groove pit on the sample is filled up by laser cladding, and X-ray flaw detection is performed after a rod-shaped tensile sample is manufactured, so that the internal defect condition of a cladding area is detected. The weld was centered on the sample. The tensile test was performed on a stretcher. The mechanical properties of the test pieces subjected to the laser cladding are shown in the following table.
The test result shows that the alloy powder which is preferably designed by laser material addition on the 12Cr2Ni4A carburizing steel matrix can obtain the tensile strength effect of more than 90 percent, ensure the safety of the airplane, prolong the service life of the airplane and have high economic benefit.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. An aircraft generator shell material-adding anti-deformation cooperative repairing method is characterized by comprising the following steps of: the method comprises the following steps:
firstly, designing an anti-deformation device according to a process parameter-heat dissipation-deformation relation, and carrying out component optimization design on the current repairing powder to prepare repairing powder;
the deformation preventing device in the step (I) comprises a base (1), a center positioning circular ring (2) arranged at the top of the base (1) and positioning blocks (3) symmetrically distributed at two sides of the center positioning circular ring (2);
the powder after the component optimization design in the step (one) comprises the following specific components: c:0.25 to 0.28 percent; mn:0.7 to 0.8 percent; cr:0.8 to 0.9 percent; si:0.8 to 0.9 percent; rare earth 0.008% -0.009%; s: less than or equal to 0.03 percent, P: less than or equal to 0.03 percent; fe: the balance;
secondly, removing defects of a part, polishing and cleaning a region to be repaired, wherein the part is an aircraft generator shell, and the material is 12Cr2Ni4A alloy steel;
thirdly, performing magnetic particle inspection detection on the area to be repaired, if the detection is unqualified, reworking to the second step until the detection is qualified, and protecting the outside of the area to be repaired by using aluminum foil;
fourthly, fixing the part to be repaired on an anti-deformation device, setting technological parameters according to the repair requirement, and spraying the repair powder prepared in the first step on the part to be repaired by using laser cladding equipment to repair;
machining the surface of the repaired part, performing magnetic flaw detection after the machining, and detecting whether a crack exists or not, and if so, repeating the steps (two) to (five) until no crack exists;
sixth, the same repair process is carried out by adopting a sample which is the same as the material of the part, and a mechanical tensile test is carried out to verify the mechanical property effect of the part;
the deformation preventing device in the step (one) is made of red copper material;
the rare earth element is at least one of Se, lu and Yb.
2. An aircraft generator housing additive deformation prevention collaborative repair method according to claim 1, characterized in that: the preparation specific process of the repair powder after the optimization design in the step (one) comprises the following steps: batching, smelting, atomizing, screening powder collection, performance analysis and testing.
3. An aircraft generator housing additive deformation prevention collaborative repair method according to claim 1, characterized in that: in the second step, polishing and cleaning are specifically as follows: cleaning by adopting a steel wire brush or a mechanical polishing tool, removing an oxide layer, leaking out metallic luster, and cleaning by using acetone.
4. An aircraft generator housing additive deformation prevention collaborative repair method according to claim 1, characterized in that: the process parameters in the step (IV) are as follows:
carrier gas: 99.999% high purity argon;
laser power: 500-800W;
scanning speed: 8-10 mm/s;
powder carrying gas: 380-400L/h;
overlap ratio: 50-60%;
spot diameter: 1.5-2.5 mm.
5. An aircraft generator housing additive deformation prevention collaborative repair method according to claim 1, characterized in that: and (fourth), cleaning the surface oxide after laser cladding one layer, and cladding the next layer after cooling to room temperature.
6. An aircraft generator housing additive deformation prevention collaborative repair method according to claim 1, characterized in that: in the fifth step, the machining treatment is specifically electric grinding head or pneumatic grinding.
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| CN102162069B (en) * | 2010-02-23 | 2013-06-19 | 宝山钢铁股份有限公司 | Flying-shear main-transmission gearwheel steel and preparation method thereof |
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| CN106544670A (en) * | 2016-11-22 | 2017-03-29 | 国营芜湖机械厂 | The preparation method of the strong low-carbon alloy steel surface laser cladding layer of superelevation and application |
| CN111074266A (en) * | 2019-12-21 | 2020-04-28 | 国营芜湖机械厂 | Rapid forming and repairing method for damage of airplane electromagnetic pure iron part accessory |
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