CN101787529A - Laser restoring method of aircraft engine cylinder body - Google Patents
Laser restoring method of aircraft engine cylinder body Download PDFInfo
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- CN101787529A CN101787529A CN 201010126861 CN201010126861A CN101787529A CN 101787529 A CN101787529 A CN 101787529A CN 201010126861 CN201010126861 CN 201010126861 CN 201010126861 A CN201010126861 A CN 201010126861A CN 101787529 A CN101787529 A CN 101787529A
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Abstract
The invention discloses a laser restoring method of an aircraft engine cylinder body, which ensures the aircraft engine cylinder body to be restored after being worn without rejection. The laser restoring method utilizes the laser energy to lead specified alloy material to be melted and coated on the part to be restored at an inner cavity of the aircraft engine cylinder body, and then leads the part to be processed in a mechanical way, thus ensuring the part to restore the physical dimension. After being restored, heat treatment is not needed to be carried out on the cylinder body, the needed hardness value can be obtained by a working surface, and the wear-resisting property is improved to some extent, so that a cylinder body which can be used again is obtained. As laser melt coating has the advantages of high bonding strength, small heat affected zone, no need of heat treatment and the like, the method is applicable to restoring the engine cylinder body. Meanwhile, in the process of the implementation, the method consumes little resource, causes no pollution and protects the environment.
Description
Technical field
The present invention relates to a kind of restorative procedure of aircraft engine cylinder body, relate in particular to a kind of laser repair method.
Background technology
At present, many aircraft engine cylinder bodies also can't be repaired after wearing and tearing, can only scrap, and cause the production cost of the enterprise that uses engine high.Cylinder body why be difficult to repair be because: 1, cylinder wall is thin, general not enough 4mm, thinnest part is 2.5mm only; 2, the cylinder body bore is little, the degree of depth is dark, and end sealing; 3, cylinder body requires that hardness is arranged, but can not heat-treat.
Summary of the invention
The invention discloses a kind of laser repair method of aircraft engine cylinder body, make the cylinder body of aircraft engine after wearing and tearing, can repair, need not to scrap.
The laser repair method of a kind of aircraft engine cylinder body of the present invention, step is as follows:
(1), remove the fatigue layer that inner chamber of cylinder block need be repaired the position, reach the state that is suitable for carrying out laser repairing, carry out penetrant inspection then, guarantee that fatigue layer removes fully with machining process;
(2), modulation powdered alloy, the granularity of powdered alloy is 50～150 μ m, and composition (wt%) is: C:0.1～0.2, Cr:14～20, Ni:2～6, Mn:0～1.5, Mo:0.5～1.5, W:0～2.5, Si:1.5～2.5, B:2.0～3.0, residue are Fe;
(3), use condenser lens that laser beam is imported inner chamber of cylinder block, send into powdered alloy synchronously, need are repaired the position carry out cladding, during cladding protection of inert gas is carried out in the molten bath; The output rating of laser apparatus is 1800～2800W during cladding, and spot diameter is Φ 3～6mm, and sweep velocity is 200～500mm/min, and amount of lap is 1.5～3mm; In this process, the cladding quality be should check at any time, defective, flaw etc. in time handled;
(4), the geometrical dimension that inner chamber of cylinder block reparation is required with machining process;
(5), carry out non-destructive test(ing)(NDT) on request.
Laser repair method of the present invention, be utilize laser energy with specific alloy material cladding to the position that the inner chamber of aircraft engine cylinder body need be repaired, and then carry out mechanical workout, make it recover geometrical dimension.Cylinder body after the reparation need not be heat-treated, and working face can obtain required hardness value, and wear resisting property increases, thereby obtains the cylinder body that can reuse.In cladding process, the engine cylinder-body base material is only surperficial little molten, and little crucible zone is no more than 0.2mm, and the heat affected zone generally is no more than 0.4mm.The alloy cladding layer of inner chamber and cylinder body base material metallurgical binding form a kind of matrix material, and bonding strength is not less than 90% of substrate intensity, and the hardness of matrix material approaches the hardness of former base material, and wear resistance is better.Cladding layer and Interface Microstructure densification, crystal grain are tiny, and defectives such as no hole, slag inclusion, crackle make the engine cylinder physical efficiency return to spendable state.
Description of drawings
Below in conjunction with the drawings and specific embodiments the present invention is done further detailed introduction:
Fig. 1 is the front view of aircraft engine cylinder body;
Fig. 2 is the left view of aircraft engine cylinder body;
Fig. 3 is that K among Fig. 1 is to view.
Embodiment
From accompanying drawing as can be known, after the inner chamber A of aircraft engine cylinder body can't use because of wearing and tearing, at this moment can adopt specific laser technology to carry out cladding, the abrading section is repaired, recover its geometrical dimension with mechanical workout then, need not thermal treatment and can obtain the engine cylinder-body that to reuse.Concrete restorative procedure is as follows:
(1), remove the fatigue layer that inner chamber of cylinder block need be repaired the position, reach the state that is suitable for carrying out laser repairing, carry out penetrant inspection then, guarantee that fatigue layer removes fully with machining process;
(2), modulation powdered alloy, the granularity of powdered alloy is 50～150 μ m, and composition (wt%) is: C:0.1～0.2, Cr:14～20, Ni:2～6, Mn:0～1.5, Mo:0.5～1.5, W:0～2.5, Si:1.5～2.5, B:2.0～3.0, residue are Fe;
(3), use condenser lens that laser beam is imported inner chamber of cylinder block, send into powdered alloy synchronously, need are repaired the position carry out cladding, during cladding protection of inert gas is carried out in the molten bath; The output rating of laser apparatus is 1800～2800W during cladding, and spot diameter is Φ 3～6mm, and sweep velocity is 200～500mm/min, and amount of lap is 1.5～3mm; In this process, the cladding quality be should check at any time, defective, flaw etc. in time handled;
(4), the geometrical dimension that inner chamber of cylinder block reparation is required with machining process;
(5), carry out non-destructive test(ing)(NDT) on request.
Wherein the rare gas element in the step (3) is generally selected argon gas for use; Every layer of cladding thickness is not more than 0.4mm in the step (3), and the cladding that can superpose on cladding layer is to reach desired thickness; Machining process in step (1) and the step (4) can be car, mill etc.Be made up of matrix material with the resulting engine cylinder-body of above-mentioned laser repair method, these two kinds of materials of the alloy cladding layer of inner chamber and cylinder body matrix are metallurgical binding, and the wear resistance of cladding layer material is higher than former cylinder body body material.Wherein the height of the composition of the powdered alloy hardness that can reach according to last requirement carries out different apolegamys.
Laser repair method of the present invention is after the wearing and tearing of the inner chamber of aircraft engine cylinder body, and the energy that utilizes laser to needing to repair the position, and then carries out machining with specific alloy material cladding, makes it recover physical dimension. Cylinder body after the reparation need not be heat-treated, and working face can obtain required hardness number, and anti-wear performance increases, thereby obtains the cylinder body that can reuse. Since laser melting coating have bond strength height, heat affected area little, the advantage such as need not to heat-treat, therefore be fit to the reparation of this kind engine cylinder-body. Simultaneously, resource consumption is few in the invention process process, and is pollution-free, environment played the effect of protection.
Claims (4)
1. the laser repair method of an aircraft engine cylinder body, step is as follows:
(1), remove the fatigue layer that inner chamber of cylinder block need be repaired the position, reach the state that is suitable for carrying out laser repairing, carry out penetrant inspection then, guarantee that fatigue layer removes fully with machining process;
(2), modulation powdered alloy, the granularity of powdered alloy is 50～150 μ m, and composition (wt%) is: C:0.1～0.2, Cr:14～20, Ni:2～6, Mn:0～1.5, Mo:0.5～1.5, W:0～2.5, Si:1.5～2.5, B:2.0～3.0, residue are Fe;
(3), use condenser lens that laser beam is imported inner chamber of cylinder block, send into powdered alloy synchronously, need are repaired the position carry out cladding, during cladding protection of inert gas is carried out in the molten bath; The output rating of laser apparatus is 1800～2800W during cladding, and spot diameter is Φ 3～6mm, and sweep velocity is 200～500mm/min, and amount of lap is 1.5～3mm; In this process, the cladding quality be should check at any time, defective, flaw etc. in time handled;
(4), the geometrical dimension that inner chamber of cylinder block reparation is required with machining process;
(5), carry out non-destructive test(ing)(NDT) on request.
2. laser repair method according to claim 1 is characterized in that: the rare gas element in the step (3) is generally selected argon gas for use.
3. laser repair method according to claim 1 is characterized in that: every layer of cladding thickness is not more than 0.4mm in the step (3), and the cladding that can superpose on cladding layer is to reach desired thickness.
4. laser repair method according to claim 1 is characterized in that: the machining process in step (1) and the step (4) can be car, mill etc.
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| CN 201010126861 CN101787529A (en) | 2010-03-18 | 2010-03-18 | Laser restoring method of aircraft engine cylinder body |
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| Application Number | Priority Date | Filing Date | Title |
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| CN 201010126861 CN101787529A (en) | 2010-03-18 | 2010-03-18 | Laser restoring method of aircraft engine cylinder body |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102059500A (en) * | 2010-11-25 | 2011-05-18 | 秦皇岛洪川实业有限公司 | Laser repairing method for tooth corona reconstructing of transmission tooth roller of single-roller crusher |
| CN102677043A (en) * | 2012-05-22 | 2012-09-19 | 山东能源机械集团大族再制造有限公司 | Upright post of hydraulic bracket and manufacturing method thereof |
| CN102677044A (en) * | 2012-05-22 | 2012-09-19 | 山东能源机械集团大族再制造有限公司 | Method of forming laser cladding layer on surface of upright post of hydraulic bracket |
| CN102677045A (en) * | 2012-05-22 | 2012-09-19 | 山东能源机械集团大族再制造有限公司 | Laser cladding method |
| CN102732831A (en) * | 2012-07-18 | 2012-10-17 | 丹阳宏图激光科技有限公司 | Laser repairing process for automobile mold |
| CN102828140A (en) * | 2012-09-20 | 2012-12-19 | 丹阳宏图激光科技有限公司 | Laser cladding repair process for valve seat |
| CN102828182A (en) * | 2012-09-20 | 2012-12-19 | 丹阳宏图激光科技有限公司 | Laser cladding repair process for gear |
| CN102828180A (en) * | 2012-09-20 | 2012-12-19 | 丹阳宏图激光科技有限公司 | Laser cladding repair process for thin-wall sleeves |
| CN102828181A (en) * | 2012-09-20 | 2012-12-19 | 丹阳宏图激光科技有限公司 | Laser cladding repair process for cross shafts |
| CN103194745A (en) * | 2012-01-09 | 2013-07-10 | 沈阳大陆激光成套设备有限公司 | Automobile reduction box shell laser restoration remanufacturing method |
| CN103909378A (en) * | 2014-04-08 | 2014-07-09 | 苏州天弘激光股份有限公司 | Optical fiber laser remanufacturing process of positive-addendum-modification large-modulus gear of ball mill |
| CN104250805A (en) * | 2013-06-28 | 2014-12-31 | 沈阳大陆激光成套设备有限公司 | Method for preparing wear-resistant heat-resistant coating through laser cladding of surface of guide roller by bar rolling mill |
| CN106011844A (en) * | 2016-06-30 | 2016-10-12 | 上海金萃激光技术有限公司 | Restoration method for valve seat sealing surface |
| CN109531045A (en) * | 2018-12-29 | 2019-03-29 | 瑞安市得力标准件制造有限公司 | Engine cylinder body spindle hole restorative procedure |
| CN109536955A (en) * | 2019-01-23 | 2019-03-29 | 南京工业大学 | Cladding mold repairing process adopting laser coaxial synchronous powder feeding method |
| CN109778183A (en) * | 2019-03-13 | 2019-05-21 | 沈阳大陆激光工程技术有限公司 | A kind of functional layer alloy material and its manufacturing method laser manufacture and remanufacture continuous casting line foot roller |
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| CN102059500A (en) * | 2010-11-25 | 2011-05-18 | 秦皇岛洪川实业有限公司 | Laser repairing method for tooth corona reconstructing of transmission tooth roller of single-roller crusher |
| CN103194745A (en) * | 2012-01-09 | 2013-07-10 | 沈阳大陆激光成套设备有限公司 | Automobile reduction box shell laser restoration remanufacturing method |
| CN103194745B (en) * | 2012-01-09 | 2015-06-24 | 沈阳大陆激光成套设备有限公司 | Automobile reduction box shell laser restoration remanufacturing method |
| CN102677043A (en) * | 2012-05-22 | 2012-09-19 | 山东能源机械集团大族再制造有限公司 | Upright post of hydraulic bracket and manufacturing method thereof |
| CN102677044A (en) * | 2012-05-22 | 2012-09-19 | 山东能源机械集团大族再制造有限公司 | Method of forming laser cladding layer on surface of upright post of hydraulic bracket |
| CN102677045A (en) * | 2012-05-22 | 2012-09-19 | 山东能源机械集团大族再制造有限公司 | Laser cladding method |
| CN102677044B (en) * | 2012-05-22 | 2014-10-01 | 山东能源机械集团大族再制造有限公司 | Method of forming laser cladding layer on surface of upright post of hydraulic bracket |
| CN102677045B (en) * | 2012-05-22 | 2014-10-01 | 山东能源机械集团大族再制造有限公司 | Laser cladding method |
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| CN102732831B (en) * | 2012-07-18 | 2014-01-15 | 丹阳宏图激光科技有限公司 | Laser repairing process for automobile mold |
| CN103668184A (en) * | 2012-07-18 | 2014-03-26 | 蒋超 | Laser repair process for automobile mould with good cladding layer organization uniformity |
| CN103668182A (en) * | 2012-07-18 | 2014-03-26 | 蒋超 | Laser repair process for automobile mould with no need of annealing |
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| CN103668184B (en) * | 2012-07-18 | 2015-08-26 | 青岛鲁强精密模具有限公司 | The laser repairing process of the vehicle mould of microstructure of surface cladding layer good uniformity |
| CN103668182B (en) * | 2012-07-18 | 2015-09-16 | 蒋超 | Without the need to the laser repairing process of the vehicle mould of annealing |
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| CN103668036B (en) * | 2012-09-20 | 2016-05-25 | 丹阳宏图激光科技有限公司 | The laser cladding repair technique of the valve seat that hardness is high and deflection is little |
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| CN103668036A (en) * | 2012-09-20 | 2014-03-26 | 丹阳宏图激光科技有限公司 | Laser cladding repairing process of valve seat with high hardness and less deformation |
| CN102828180A (en) * | 2012-09-20 | 2012-12-19 | 丹阳宏图激光科技有限公司 | Laser cladding repair process for thin-wall sleeves |
| CN102828182A (en) * | 2012-09-20 | 2012-12-19 | 丹阳宏图激光科技有限公司 | Laser cladding repair process for gear |
| CN104250805A (en) * | 2013-06-28 | 2014-12-31 | 沈阳大陆激光成套设备有限公司 | Method for preparing wear-resistant heat-resistant coating through laser cladding of surface of guide roller by bar rolling mill |
| CN103909378A (en) * | 2014-04-08 | 2014-07-09 | 苏州天弘激光股份有限公司 | Optical fiber laser remanufacturing process of positive-addendum-modification large-modulus gear of ball mill |
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| CN106011844A (en) * | 2016-06-30 | 2016-10-12 | 上海金萃激光技术有限公司 | Restoration method for valve seat sealing surface |
| CN106011844B (en) * | 2016-06-30 | 2018-05-04 | 上海金萃激光技术有限公司 | A kind of restorative procedure of porthole sealing surface of seat |
| CN109531045A (en) * | 2018-12-29 | 2019-03-29 | 瑞安市得力标准件制造有限公司 | Engine cylinder body spindle hole restorative procedure |
| CN109536955A (en) * | 2019-01-23 | 2019-03-29 | 南京工业大学 | Cladding mold repairing process adopting laser coaxial synchronous powder feeding method |
| CN109778183A (en) * | 2019-03-13 | 2019-05-21 | 沈阳大陆激光工程技术有限公司 | A kind of functional layer alloy material and its manufacturing method laser manufacture and remanufacture continuous casting line foot roller |
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Inventor after: Wang Weifei Inventor after: Li Wenhua Inventor after: Cai Deming Inventor after: Han Xiaoming Inventor after: Wang Guosheng Inventor after: Zhang Yiwu Inventor after: Zheng Daiqun Inventor before: Wang Weifei Inventor before: Li Wenhua Inventor before: Cai Deming Inventor before: Han Xiaoming Inventor before: Wang Guosheng Inventor before: Zhang Yiwu |
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Open date: 20100728 |