CN111745159A - Laser additive repair method for titanium alloy undercarriage upper stay bar fit out-of-tolerance - Google Patents
Laser additive repair method for titanium alloy undercarriage upper stay bar fit out-of-tolerance Download PDFInfo
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- CN111745159A CN111745159A CN202010526177.0A CN202010526177A CN111745159A CN 111745159 A CN111745159 A CN 111745159A CN 202010526177 A CN202010526177 A CN 202010526177A CN 111745159 A CN111745159 A CN 111745159A
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- repair
- stay bar
- tolerance
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- laser additive
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y40/00—Auxiliary operations or equipment, e.g. for material handling
- B33Y40/20—Post-treatment, e.g. curing, coating or polishing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/247—Removing material: carving, cleaning, grinding, hobbing, honing, lapping, polishing, milling, shaving, skiving, turning the surface
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Abstract
The invention relates to a laser additive repair method for titanium alloy undercarriage upper stay bar fit out-of-tolerance, belonging to the technical field of additive manufacturing; aiming at parts of TC18, the method selects TC18 powder with the same composition as a repair material, is provided with an atmosphere protection device, adopts optimized laser additive process parameters to repair an out-of-tolerance area, and then carries out local heat treatment on the repair area; the repaired part has no crack defect, the surface has no oxidation, the gap between the stay bar and the hook ring is eliminated after the stay bar and the hook ring are matched and repaired, the position precision is ensured, and the landing effect of the airplane is improved.
Description
Technical Field
The invention relates to a laser additive repair method for the over-tolerance of the matching of a stay bar on a titanium alloy undercarriage, belongs to the technical field of additive manufacturing, and is mainly used for maintaining the over-tolerance of the matching of the stay bar on an airplane.
Background
A certain type of aircraft landing gear is found in the maintenance process, when the main landing gear is put down, the main landing gear can be folded to lock the stay bar, the stay bar is kept at the position, the clearance between the upper stay bar and the lower stay bar is too large, the main landing gear is poor in putting down position fixation, the inner position and the outer position can be shaken, the aircraft landing effect is reduced, the arc surface of the upper stay bar bears huge load in the taking-off and landing process of the aircraft, the gap is shaken, the part can be abraded, and the service life of the part is shortened. Maintenance should therefore ensure that the play between the struts is eliminated.
In the prior art, argon arc welding repair is usually used for repairing the matching surface of a part in an out-of-tolerance mode and then cutting machining is carried out, and the repair of small-size defects is not easy to control due to the fact that the repair amount of the argon arc welding repair is large in technological characteristics, so that the follow-up machining allowance is large, and the repair period is too long. And laser vibration material disk restoration, the minimum restoration size is laser facula size, and restoration thickness can be controlled by the powder feed volume simultaneously, does not leave too much machining allowance, is fit for the assembly iteration restoration to the fitting surface.
Disclosure of Invention
The invention provides a laser additive repair method for the out-of-tolerance of the matching surface of a stay bar on a titanium alloy undercarriage, and aims to repair the out-of-tolerance defect of the matching surface of the stay bar on titanium alloy of a certain airplane.
The technical scheme of the invention comprises the following specific contents:
the utility model provides a titanium alloy undercarriage stay bar cooperation out-of-tolerance laser vibration material disk repair method, what mainly aim at is the undercarriage stay bar that the material is TC18, its characterized in that: the method comprises the following steps:
1) selecting TC18 laser additive powder with the same components;
2) polishing and cleaning before repairing to expose metallic luster;
3) fixing, clamping and atmosphere protection: clamping a part by using a tool clamp, and simultaneously additionally arranging an atmosphere protection device on an area to be repaired;
4) laser additive repair: recovering the out-of-tolerance size of the matching surface of the upper support rod by adopting a laser additive process;
5) heat treatment after repair: wrapping the repair area by using a ceramic heating belt, performing local heat treatment at the temperature of 550 ℃ and 650 ℃, preserving heat for 2h, and slowly cooling;
6) appearance and fluorescence detection: visual inspection is adopted for the appearance of the additive repair area, the repair layer is smooth and completely covers the defect area, and no obvious oxidation color exists; and the additive repairing layer is subjected to fluorescence detection, and the surface has no crack or unfused defect.
7) And (3) manual polishing and assembling: and (4) manually grinding the repair area according to the size requirement, and repairing the stay bar and the shackle to ensure that the clearance between the stay bar fits is eliminated, if a local out-of-tolerance gap still exists, returning to the step (4) to repair again until the assembly tolerance requirement is met, and finally completing part repair and assembly.
The granularity of the TC18 laser additive powder in the step 1) is 53-106 mu m.
The TC18 laser additive powder is prepared by an air atomization method or a rotary electrode method.
The TC18 laser additive powder is fed by a vibrating powder feeder.
Polishing and cleaning before repairing in the step 1); and processing the area to be repaired by adopting a handheld polishing gun, and wiping the surface with alcohol or acetone to remove oil stains.
The laser material increase process parameters in the step 4) are as follows: the laser power is 400-600W, the scanning speed is 5-12 mm/s, the powder feeding amount is 3-8g/min, the Ar powder feeding flow is 3-5L/min, the Ar protective gas flow is 15-20L/min, and the overlapping rate of adjacent forming channels is 40-50%.
The thickness of the single layer formed by laser is controlled to be 0.1-0.3 mm.
The laser forming path is scanned along a direction in which the local defect is longer.
The invention has the beneficial effects that:
the upper stay bar part is made of TC18 titanium alloy, the TC18 titanium alloy has excellent performance, such as stronger tensile capacity and better toughness, is mainly used for manufacturing large-scale bearing structural members on an airplane body and an undercarriage, the alloy has better weldability and formability, and can be repaired by using the same material.
The out-of-tolerance clearance of the circular arc surface of the upper stay bar part is 0.5mm, and the accumulation repair can be carried out by adopting an additive mode. Through laser material increase repair of the arc surface of the upper support rod, the support rod and the hook ring are matched and repaired, so that the clearance between the upper support rod and the lower support rod is eliminated, and the purpose of firmness in the down position of the main undercarriage is achieved. In the repairing process, the additive scanning speed is strictly controlled, the heat input is reduced, and the comprehensive performance reduction of a repairing area caused by the overlarge heat affected zone of the joint due to the accumulation of the heat input is avoided. Therefore, the method is suitable for repairing the defect area by adopting a laser additive manufacturing mode, compared with manual argon arc welding repair, the laser additive repair can accurately control the repair speed, the single-layer growth amount and the machining allowance of 0.1-0.3mm, and provides convenience for subsequent manual grinding and repairing of parts.
By using the laser additive manufacturing method, a laser deposition additive test is carried out on a forging TC18 test plate, and the microstructure, the hardness and the room-temperature mechanical property of a sample are tested. The results show that: the deposited layer and the matrix are fused well, and the tissue has no crack, air hole and unfused defect; the hardness of the deposition repair area can reach 400HV, is higher than that of the parent metal by about 50HV and is approximately provided with a heat affected area with the thickness of 0.4mm, and the hardness of the heat affected area is close to that of the parent metal; after the deposited repairing sample is annealed, the tensile strength at room temperature can reach 1125MPa, which is slightly higher than that of the parent metal 1117MPa, thereby ensuring the strength of the repaired joint and prolonging the service life.
Drawings
FIG. 1TC18 schematic diagram of laser additive repair layer
FIG. 2 is a schematic view of the circular arc fitting surface structure of the upper stay bar
Detailed Description
The technical scheme of the invention is further detailed by combining the following examples:
analyzing the defect condition of the upper stay bar to be repaired, confirming the distribution and the size of the defect position, determining the need of powder materials and repair equipment, and implementing the following specific steps through the analysis:
(1) a laser additive powder with composition TC18 was selected. The deposited powder with the same components is selected, the granularity is 53-106 mu m, and good metallurgical bonding is ensured to be formed after repair. The equipment adopts a vibrating powder feeder to ensure stable powder feeding.
(2) And polishing and cleaning before repairing. And processing the area to be repaired by adopting a handheld polishing gun, exposing the metallic luster, and wiping the surface by using alcohol or acetone to remove oil stains.
(3) And fixing, clamping and atmosphere protection. And clamping the part by using a tool clamp, and additionally arranging an atmosphere protection device on the area to be repaired. The repairing equipment uses a six-axis robot, so that the robot cannot interfere with the protection device and the clamp in the repairing process.
(4) And (5) laser additive repair. Recovering the out-of-tolerance size of the matching surface of the upper support rod, wherein the laser material increase process parameters are as follows: the laser power is 400-600W, the scanning speed is 5-12 mm/s, the powder feeding amount is 3-8g/min, the Ar powder feeding flow is 3-5L/min, the Ar protective gas flow is 15-20L/min, the lap joint rate of adjacent forming channels is 40-50%, the thickness of a single layer formed by laser is controlled to be 0.1-0.3mm, a forming path is required to be scanned along the longer direction of a local defect, the local temperature is prevented from being too high, and surface oxidation is prevented.
(5) And (4) carrying out heat treatment after repairing. And (3) wrapping the repair area by using a ceramic heating belt, performing local heat treatment at 550 ℃ and 650 ℃, preserving heat for 2h, and slowly cooling the heat treatment area wrapped by asbestos.
(6) Appearance and fluorescence detection. Visual inspection of the additive repair area should level the repair layer completely covering the defect area without significant oxidation. And (4) detecting the additive repairing layer by fluorescence detection, wherein the surface is required to have no crack or fusion defect.
(7) And (6) manually polishing and assembling. And (4) manually grinding the repair area according to the size requirement, and repairing the stay bar and the shackle to ensure that the clearance between the stay bar fits is eliminated, if a local out-of-tolerance gap still exists, returning to the step (4) to repair again until the assembly tolerance requirement is met, and finally completing part repair and assembly.
Example 1
And repairing the over-tolerance defect of the strut on a certain airplane by adopting laser material increase.
The upper stay bar of a certain type of airplane is forged by titanium alloy and made of TC18, after the airplane undergoes an overhaul period, when the main landing gear is put down, the clearance between the upper stay bar and the lower stay bar is overlarge, and the out-of-tolerance size of a local area reaches 0.5 mm.
The selected component is TC18 powder prepared by gas atomization method or rotary electrode method, and the particle size is 53-106 μm. The TC18 powder has good weldability and formability, is suitable for additive repair of titanium alloy, and ensures good metallurgical bonding after repair. The equipment adopts a vibrating powder feeder to ensure stable powder feeding.
And polishing and cleaning before repairing. And (3) polishing the worn area of the matching surface by using a handheld polishing gun, removing the corrosion layer on the surface to expose the metallic luster, and wiping the surface by using alcohol or acetone to remove oil stains.
And fixing, clamping and atmosphere protection. The tool clamp is adopted to clamp the part, and the atmosphere protection device is additionally arranged on the area to be repaired at the same time, so that the material increase equipment, the protection device and the clamp cannot interfere in the repairing process, the protection atmosphere is introduced before repairing, and the protector is fully filled in the device.
Laser additive repair: the repair equipment uses a six-axis robot, is provided with a 5000w laser system and a coaxial powder feeding system, adopts multilayer cladding, and adopts the dimension technological parameters of the support rod matching surface out-of-tolerance in the material increase recovery as follows: the laser power is 400-500W, the scanning speed is 10-12 mm/s, the powder feeding amount is 6g/min, the Ar powder feeding flow is 5L/min, the Ar protective gas flow is 15L/min, the lap joint rate of adjacent forming channels is 50%, the thickness of a single layer formed by laser is controlled to be 0.1-0.3mm, a repair allowance of 0.3mm is reserved in an additive repair area, a forming path is scanned along the longer direction of a local defect, the local temperature is prevented from being overhigh, and surface oxidation is prevented. And selecting different laser powers and scanning rates according to the sizes of the surface defects of the parts.
And (4) carrying out heat treatment after repairing. And wrapping the repair area by using a ceramic heating belt, performing local heat treatment, heating to 650 ℃, preserving heat for 2 hours, and slowly cooling along with the furnace by additionally arranging an asbestos-wrapped heat treatment area.
Appearance and fluorescence detection. Visual inspection of the additive repair area should level the repair layer completely covering the defect area without significant oxidation. And (4) detecting the additive repairing layer by fluorescence detection, wherein the surface is required to have no crack or fusion defect.
And (6) manually polishing and assembling. According to the drawing size requirement, grinding the part, removing additive machining allowance, matching and repairing the stay bar and the shackle, wherein the circular arc matching surface of the stay bar is shown in figure 2, if the local size is out of tolerance, returning to laser additive repair until the size meets the drawing requirement, assembling stably, polishing the surface, ensuring that the part rotates smoothly, and assembling and applying the part in a machine.
The existing repair of the over-tolerance matching by argon arc welding can cause overlarge repair allowance, and a machine tool is required to be used for cutting, so that the repair period is longer. The repaired microstructure is dense without pores and unfused defects, as shown in fig. 1. And 4, carrying out fluorescence detection on the additive repair part without crack defects.
Claims (8)
1. The utility model provides a titanium alloy undercarriage stay bar cooperation out-of-tolerance laser vibration material disk repair method, what mainly aim at is the undercarriage stay bar that the material is TC18, its characterized in that: the method comprises the following steps:
1) selecting TC18 laser additive powder with the same components;
2) polishing and cleaning before repairing to expose metallic luster;
3) fixing, clamping and atmosphere protection: clamping a part by using a tool clamp, and simultaneously additionally arranging an atmosphere protection device on an area to be repaired;
4) laser additive repair: recovering the out-of-tolerance size of the matching surface of the upper support rod by adopting a laser additive process;
5) heat treatment after repair: wrapping the repair area by using a ceramic heating belt, performing local heat treatment at the temperature of 550 ℃ and 650 ℃, preserving heat for 2h, and slowly cooling;
6) appearance and fluorescence detection: visual inspection is adopted for the appearance of the additive repair area, the repair layer is smooth and completely covers the defect area, and no obvious oxidation color exists; and the additive repairing layer is subjected to fluorescence detection, and the surface has no crack or unfused defect.
7) And (3) manual polishing and assembling: and (4) manually grinding the repair area according to the size requirement, and repairing the stay bar and the shackle to ensure that the clearance between the stay bar fits is eliminated, if a local out-of-tolerance gap still exists, returning to the step (4) to repair again until the assembly tolerance requirement is met, and finally completing part repair and assembly.
2. The laser additive repair method for titanium alloy landing gear stay bar fit out-of-tolerance according to claim 1, wherein the step 1) TC18 laser additive powder particle size is 53-106 μm.
3. The laser additive repair method for titanium alloy landing gear stay bar fit out-of-tolerance according to claim 1, wherein the TC18 laser additive powder is prepared by an air atomization method or a rotary electrode method.
4. The laser additive repair method for titanium alloy landing gear stay rod fit out-of-tolerance according to claim 1, wherein the TC18 laser additive powder is fed by a vibrating powder feeder.
5. The laser additive repair method for titanium alloy undercarriage stay bar fit out-of-tolerance according to claim 1, wherein the step 1) is grinding and cleaning before repair; and processing the area to be repaired by adopting a handheld polishing gun, and wiping the surface with alcohol or acetone to remove oil stains.
6. The laser additive repair method for titanium alloy undercarriage stay bar fit out-of-tolerance according to claim 1, wherein the laser additive process parameters of the step 4) are as follows: the laser power is 400-600W, the scanning speed is 5-12 mm/s, the powder feeding amount is 3-8g/min, the Ar powder feeding flow is 3-5L/min, the Ar protective gas flow is 15-20L/min, and the overlapping rate of adjacent forming channels is 40-50%.
7. The laser additive repair method for titanium alloy landing gear stay bar fit out-of-tolerance according to claim 1, wherein the thickness of the laser-formed single layer in the step 4) is controlled to be 0.1-0.3 mm.
8. The laser additive repair method for titanium alloy landing gear stay-on-landing gear fit out-of-tolerance according to claim 1, wherein the laser forming path of step 4) is scanned along a direction in which the local defect is longer.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010526177.0A CN111745159A (en) | 2020-06-10 | 2020-06-10 | Laser additive repair method for titanium alloy undercarriage upper stay bar fit out-of-tolerance |
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| CN202010526177.0A CN111745159A (en) | 2020-06-10 | 2020-06-10 | Laser additive repair method for titanium alloy undercarriage upper stay bar fit out-of-tolerance |
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Citations (5)
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|---|---|---|---|---|
| CN103114286A (en) * | 2013-02-27 | 2013-05-22 | 沈阳航空航天大学 | Method for repairing titanium alloy by ultrasound-assisted laser |
| CN103949757A (en) * | 2014-05-08 | 2014-07-30 | 中国航空工业集团公司北京航空材料研究院 | Process for repairing pits in titanium alloy aircraft sliding rail in argon arc welding way |
| CN107675167A (en) * | 2017-09-04 | 2018-02-09 | 中国航发北京航空材料研究院 | A kind of superhigh intensity steel member ultrasonic impact auxiliary laser cladding restorative procedure |
| CN109267063A (en) * | 2018-11-06 | 2019-01-25 | 成都飞机工业（集团）有限责任公司 | A method of titanium alloy is repaired based on laser melting coating and forges beam surface defect |
| CN110983103A (en) * | 2019-12-05 | 2020-04-10 | 江西瑞曼增材科技有限公司 | 3D printing laser repair method for TB6 titanium alloy |
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2020
- 2020-06-10 CN CN202010526177.0A patent/CN111745159A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103114286A (en) * | 2013-02-27 | 2013-05-22 | 沈阳航空航天大学 | Method for repairing titanium alloy by ultrasound-assisted laser |
| CN103949757A (en) * | 2014-05-08 | 2014-07-30 | 中国航空工业集团公司北京航空材料研究院 | Process for repairing pits in titanium alloy aircraft sliding rail in argon arc welding way |
| CN107675167A (en) * | 2017-09-04 | 2018-02-09 | 中国航发北京航空材料研究院 | A kind of superhigh intensity steel member ultrasonic impact auxiliary laser cladding restorative procedure |
| CN109267063A (en) * | 2018-11-06 | 2019-01-25 | 成都飞机工业（集团）有限责任公司 | A method of titanium alloy is repaired based on laser melting coating and forges beam surface defect |
| CN110983103A (en) * | 2019-12-05 | 2020-04-10 | 江西瑞曼增材科技有限公司 | 3D printing laser repair method for TB6 titanium alloy |
Non-Patent Citations (1)
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