CN105695986A - System and method for repairing nickel-based monocrystal high-temperature alloy turbine blade tip - Google Patents
System and method for repairing nickel-based monocrystal high-temperature alloy turbine blade tip Download PDFInfo
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- CN105695986A CN105695986A CN201610102929.4A CN201610102929A CN105695986A CN 105695986 A CN105695986 A CN 105695986A CN 201610102929 A CN201610102929 A CN 201610102929A CN 105695986 A CN105695986 A CN 105695986A
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- single crystal
- blade
- blade tip
- turbine blade
- nickel
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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
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- 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
- C23C24/106—Coating with metal alloys or metal elements only
Abstract
The invention provides a system and method for repairing a nickel-based monocrystal high-temperature alloy turbine blade tip. The system comprises a laser device, a powder feeder, a mechanical arm, a controller, a positioner and a coaxial powder feeding cladding head. The method comprises the steps that a monocrystal turbine blade to be repaired is ground, cleaned and fixed to the positioner through a clamp, the laser device and the powder feeder are connected to the coaxial powder feeding cladding head, the coaxial powder feeding cladding head is fixed to the mechanical arm and is perpendicular to the surface of the monocrystal turbine blade tip, and the controller controls the motion path of the mechanical arm. By the adoption of the system and method for repairing the nickel-based monocrystal high-temperature alloy turbine blade tip, the monocrystal turbine blade tip can be successfully repaired through net shaping, the interior of the repaired monocrystal blade tip is compact and continuous monocrystal structures, and the using requirements of the monocrystal blade can be completely met through subsequent machining.
Description
Technical field
The present invention relates to laser repairing and Fine Texture of Material growth field, and particularly to a kind of system and method repairing nickel-base high-temperature single crystal alloy turbo blade blade tip。
Background technology
Along with modern aeroengine improving constantly for operating temperature, nickel-base high-temperature single crystal alloy has been widely used for manufacturing turbine high temperature blade。Crystal Nickel-based Superalloy turbo blade price is high, and every unit price reaches 30,000 dollars。Due to aero-engine work under bad environment, its blade tip position easily produces the defects such as abrasion, burn into crackle, material deficiency。The service life being extended single crystal turbine blade by recovery technique can reduce aero-engine maintenance cost, saves expensive material, produces huge economic benefit。Renovation technique step specifically includes that the detection of leaf cleaning, vane tip, crackle are cleaned and polishing, reparation, machining allowance and detection。
Current laser powder feeding melting and coating technique has been used to clean molding and repairs polycrystalline and column crystal blade, but is difficult to repair nickel-based monocrystal turbine blade-tip。Its Major Difficulties obtains continuous print single crystal organization in the blade tip of spreading。The lattice of nickel-base high-temperature single crystal alloy is face-centered cubic, has epitaxial growth characteristic (under uniform temperature gradient, columnar dendrite can grow always) along certain crystal orientation。In single crystal turbine blade tip surface during laser melting coating monocrystal nickel-base high-temperature alloy, along with the solidification in molten bath, the crystal orientation with single crystal blade blade tip is grown by columnar dendrite for epitaxial growth direction。By the impact of melting pool shape and thermograde, when columnar dendrite grows into certain altitude, equiaxed grain structure there will be and stop columnar dendrite continued growth。In multilamellar cladding process, equiaxed grain structure can block columnar dendrite and grow continuously further up, and produces crystal boundary between equiax crystal and columnar dendrite。Owing to nickel-base high-temperature single crystal alloy lacks boundary-strengthening element。Once there is crystal boundary, under bigger thermal stress, very easily there is crackle and along crystal boundary extending in grain boundaries, directly affects the performance repairing rear blade, it is difficult to meet the reparation requirement of single crystal blade。Therefore, in multilamellar even the blade tip process of multilamellar multi-pass laser cladding reblading, complete remelting is fallen equiaxed grain structure and is to ensure that in restoring area to obtain the key of whole single crystal organization。Therefore, when laser repairing nickel-based monocrystal turbo blade blade tip, according to blade tip width and heat conduction ring border, local, accurately control melting pool shape and thermograde in real time, thus ensureing in the blade tip repaired as single crystal organization completely, meet the reparation requirement of single crystal turbine blade。
Summary of the invention
The present invention proposes a kind of system and method repairing nickel-base high-temperature single crystal alloy turbo blade blade tip, successfully clean molding can repair out the blade tip of single crystal turbine blade, it is all fine and closely woven continuous print columnar dendrite in single crystal blade blade tip after reparation, is fully met the instructions for use of single crystal blade by follow-up machining。
In order to achieve the above object, the present invention proposes a kind of system repairing nickel-base high-temperature single crystal alloy turbo blade blade tip, including laser instrument, powder feeder, mechanical arm, controller, deflection machine and coaxial powder-feeding cladding head, wherein said single crystal turbine blade to be repaired is fixed on deflection machine by fixture after polishing cleaning, laser instrument and powder feeder access coaxial powder-feeding cladding head, and coaxial powder-feeding cladding head is fixing on the robotic arm, and described controller controls the movement locus of mechanical arm。
Further, described coaxial powder-feeding cladding head is perpendicular to the top end surface of single crystal turbine blade blade tip。
Further, the process parameters range of described repair system is: laser power 50W 5000W, and spot diameter is 0.5mm 3mm, scanning speed 5mm/s 500mm/s, and powder feeding rate is 1g/min 30g/min, and defocusing amount is-10mm 10mm。
In order to achieve the above object, the present invention also proposes a kind of method repairing nickel-base high-temperature single crystal alloy turbo blade blade tip, comprises the following steps:
Line cutting is adopted to remove the original impaired blade tip of single crystal turbine blade to be repaired；
Adopt the top end surface of sand papering single crystal turbine blade blade tip to be repaired；
Use the top end surface of the single crystal turbine blade blade tip to be repaired after acetone and alcohol washes polishing；
By fixture, described single crystal turbine blade to be repaired is fixed on deflection machine；
Coaxial powder-feeding laser melting coating head is fixed on the robotic arm；
Motion path and the attitude of mechanical arm is calculated according to single crystal turbine blade blade tip shapometer；
Mechanical arm drives the motion of coaxial powder-feeding laser melting coating head according to the movement locus set, and single crystal turbine blade carries out blade tip spreading reparation。
Further, the top end surface of described employing sand papering single crystal turbine blade blade tip to be repaired to roughness less than 50 microns。
Further, use coaxial argon that single crystal turbine blade is protected in laser repairing single crystal turbine blade process。
Further, in laser repairing single crystal turbine blade process, laser power, scanning speed and defocusing amount adjust according to blade tip width Real-time and Dynamic。
Further, the process parameters range of described laser repairing is: laser power 50W 5000W, and spot diameter is 0.5mm 3mm, scanning speed 5mm/s 500mm/s, and powder feeding rate is 1g/min 30g/min, and defocusing amount is-10mm 10mm。
The present invention proposes a kind of system and method repairing nickel-base high-temperature single crystal alloy turbo blade blade tip, in laser repairing single crystal turbine blade process, by regulating the technological parameter of laser power, scanning speed and defocusing amount etc. so that laser facula is along with blade tip width real-time change。Measuring blade tip width calculate defocusing amount by certain mathematical relationship in advance, and the change according to laser power and scanning speed regulates in real time, thus ensureing that the blade tip of spreading is consistent with original blade tip width, the blade tip of reparation is interior is continuous single crystal organization completely。The present invention successfully clean molding can repair out the blade tip of single crystal turbine blade, is all fine and closely woven continuous print single crystal organization, is fully met the instructions for use of single crystal blade by follow-up machining in the single crystal blade after reparation。
Accompanying drawing explanation
Fig. 1 show the coaxial powder-feeding laser melting coating header structure schematic diagram of present pre-ferred embodiments。
Fig. 2 show the method flow diagram repairing nickel-base high-temperature single crystal alloy turbo blade blade tip of present pre-ferred embodiments。
Fig. 3 show the single crystal turbine blade design sketch after the reparation of present pre-ferred embodiments。
Detailed description of the invention
Provide the specific embodiment of the present invention below in conjunction with accompanying drawing, but the invention is not restricted to following embodiment。According to the following describes and claims, advantages and features of the invention will be apparent from。It should be noted that, accompanying drawing all adopts the form simplified very much and all uses non-ratio accurately, is only used for convenient, to aid in illustrating the embodiment of the present invention lucidly purpose。
Refer to Fig. 1, Fig. 1 and show the coaxial powder-feeding laser melting coating header structure schematic diagram of present pre-ferred embodiments。The present invention proposes a kind of system repairing nickel-base high-temperature single crystal alloy turbo blade blade tip, including laser instrument, powder feeder, mechanical arm, controller, deflection machine and coaxial powder-feeding cladding head, wherein said single crystal turbine blade to be repaired 100 is fixed on deflection machine by fixture, laser instrument and powder feeder access coaxial powder-feeding cladding head, coaxial powder-feeding cladding head is fixing on the robotic arm, and described controller controls the movement locus of mechanical arm。
According to present pre-ferred embodiments, described mechanical arm is 6 shaft mechanical arms, and described laser instrument and powder feeder access coaxial powder-feeding laser melting coating head 200。Further, when laser repairing single crystal turbine blade blade tip, described coaxial powder-feeding laser melting coating head is perpendicular to the top end surface of single crystal turbine blade blade tip。
Owing to turbo blade blade tip diverse location width is inconsistent, in laser repairing single crystal turbine blade process, laser power, scanning speed and defocusing amount adjust according to blade tip width Real-time and Dynamic。The process parameters range of described repair system is: laser power 50W 5000W, and spot diameter is 0.5mm 3mm, scanning speed 5mm/s 500mm/s, and powder feeding rate is 1g/min 30g/min, and defocusing amount is-10mm 10mm。
Refer to Fig. 2, Fig. 2 again and show the method flow diagram repairing nickel-base high-temperature single crystal alloy turbo blade blade tip of present pre-ferred embodiments。The present invention also proposes a kind of method repairing nickel-base high-temperature single crystal alloy turbo blade blade tip, comprises the following steps:
Step S100: adopt line cutting to remove the original impaired blade tip of blade to be repaired；
Step S200: adopt the top end surface of sand papering single crystal turbine blade blade tip to be repaired；
Step S300: use the top end surface of the single crystal turbine blade blade tip to be repaired after acetone and alcohol washes polishing；
Step S400: described single crystal turbine blade to be repaired is fixed on deflection machine by fixture；
Step S500: coaxial powder-feeding laser melting coating head is fixed on the robotic arm；
Step S600: calculate motion path and the attitude of mechanical arm according to single crystal turbine blade blade tip shapometer；
Step S700: mechanical arm drives the motion of coaxial powder-feeding laser melting coating head according to the movement locus set, and single crystal turbine blade carries out blade tip spreading reparation。
According to present pre-ferred embodiments, use coaxial argon that single crystal turbine blade is protected in laser repairing single crystal turbine blade process。
Owing to turbo blade blade tip diverse location width is inconsistent, in laser repairing single crystal turbine blade process, laser power, scanning speed and defocusing amount adjust according to blade tip width Real-time and Dynamic。The process parameters range of described laser repairing is: laser power 50W 5000W, and spot diameter is 0.5mm 3mm, scanning speed 5mm/s 500mm/s, and powder feeding rate is 1g/min 30g/min, and defocusing amount is-10mm 10mm。
In sum, the present invention proposes a kind of system and method repairing nickel-base high-temperature single crystal alloy turbo blade blade tip, in laser repairing single crystal turbine blade process, by regulating the technological parameter of laser power, scanning speed and defocusing amount etc. so that laser facula is along with blade tip width real-time change。Measuring blade tip width calculate defocusing amount by certain mathematical relationship in advance, and the change according to laser power and scanning speed regulates in real time, thus ensureing that the blade tip of spreading is consistent with original blade tip width, the blade tip of reparation is interior is continuous single crystal organization completely。The present invention successfully clean molding can repair out the blade tip of single crystal turbine blade, is all fine and closely woven continuous print single crystal organization, is fully met the instructions for use of single crystal blade by follow-up machining in the single crystal blade after reparation。Fig. 3 show the single crystal turbine blade design sketch after the reparation of present pre-ferred embodiments。
Although the present invention is disclosed above with preferred embodiment, so it is not limited to the present invention。Persond having ordinary knowledge in the technical field of the present invention, without departing from the spirit and scope of the present invention, when being used for a variety of modifications and variations。Therefore, protection scope of the present invention is when being as the criterion depending on those as defined in claim。
Claims (8)
1. the system repairing nickel-base high-temperature single crystal alloy turbo blade blade tip, it is characterized in that, including laser instrument, powder feeder, mechanical arm, controller, deflection machine and coaxial powder-feeding cladding head, wherein said single crystal turbine blade to be repaired is fixed on deflection machine by fixture after polishing cleaning, laser instrument and powder feeder access coaxial powder-feeding cladding head, and coaxial powder-feeding cladding head is fixing on the robotic arm, and described controller controls the movement locus of mechanical arm。
2. the system of reparation nickel-base high-temperature single crystal alloy turbo blade blade tip according to claim 1, it is characterised in that described coaxial powder-feeding cladding head is perpendicular to the top end surface of single crystal turbine blade blade tip。
3. the system of reparation nickel-base high-temperature single crystal alloy turbo blade blade tip according to claim 1, it is characterized in that, the process parameters range of described repair system is: laser power 50W 5000W, spot diameter is 0.5mm 3mm, scanning speed 5mm/s 500mm/s, powder feeding rate is 1g/min 30g/min, and defocusing amount is-10mm 10mm。
4. the method repairing nickel-base high-temperature single crystal alloy turbo blade blade tip, it is characterised in that comprise the following steps:
Line cutting is adopted to remove the original impaired blade tip of single crystal turbine blade to be repaired；
Adopt the top end surface of sand papering single crystal turbine blade blade tip to be repaired；
Use the top end surface of the single crystal turbine blade blade tip to be repaired after acetone and alcohol washes polishing；
By fixture, described single crystal turbine blade to be repaired is fixed on deflection machine；
Coaxial powder-feeding laser melting coating head is fixed on the robotic arm；
Motion path and the attitude of mechanical arm is calculated according to single crystal turbine blade blade tip shapometer；
Mechanical arm drives the motion of coaxial powder-feeding laser melting coating head according to the movement locus set, and single crystal turbine blade carries out blade tip spreading reparation。
5. the method for reparation nickel-base high-temperature single crystal alloy turbo blade blade tip according to claim 4, it is characterised in that the top end surface of described employing sand papering single crystal turbine blade blade tip to be repaired to roughness less than 50 microns。
6. the method for reparation nickel-base high-temperature single crystal alloy turbo blade blade tip according to claim 4, it is characterised in that use coaxial argon that single crystal turbine blade is protected in laser repairing single crystal turbine blade process。
7. the method for reparation nickel-base high-temperature single crystal alloy turbo blade blade tip according to claim 4, it is characterised in that in laser repairing single crystal turbine blade process, laser power, scanning speed and defocusing amount adjust according to blade tip width Real-time and Dynamic。
8. the method for reparation nickel-base high-temperature single crystal alloy turbo blade blade tip according to claim 4, it is characterized in that, the process parameters range of described laser repairing is: laser power 50W 5000W, spot diameter is 0.5mm 3mm, scanning speed 5mm/s 500mm/s, powder feeding rate is 1g/min 30g/min, and defocusing amount is-10mm 10mm。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610102929.4A CN105695986A (en) | 2016-02-25 | 2016-02-25 | System and method for repairing nickel-based monocrystal high-temperature alloy turbine blade tip |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610102929.4A CN105695986A (en) | 2016-02-25 | 2016-02-25 | System and method for repairing nickel-based monocrystal high-temperature alloy turbine blade tip |
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| CN201610102929.4A Pending CN105695986A (en) | 2016-02-25 | 2016-02-25 | System and method for repairing nickel-based monocrystal high-temperature alloy turbine blade tip |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106077647A (en) * | 2016-07-27 | 2016-11-09 | 湖南大学 | A kind of laser gain material controls the method for fragility Laves phase during manufacturing nickel base superalloy |
| CN108115249A (en) * | 2017-12-29 | 2018-06-05 | 西安交通大学 | A kind of system for repairing monocrystalline or orienting peritectic alloy blade |
| CN108213832A (en) * | 2017-12-29 | 2018-06-29 | 西安交通大学 | A kind of restorative procedure realized monocrystalline or orient peritectic alloy blade inner flow passage complex |
| CN110055526A (en) * | 2019-04-18 | 2019-07-26 | 江西省科学院应用物理研究所 | A kind of single crystal super alloy laser epitaxial growth restorative procedure of energy constraint |
| CN111360251A (en) * | 2020-02-10 | 2020-07-03 | 中国科学院金属研究所 | Method for repairing single crystal high-temperature alloy thin-walled workpiece through powder feeding pulse laser 3D printing |
| CN111745160A (en) * | 2020-07-08 | 2020-10-09 | 哈尔滨工业大学 | Method for eliminating heat cracks in single crystal high-temperature alloy repair process under assistance of magnetic field |
| CN112122617A (en) * | 2020-08-21 | 2020-12-25 | 苏州华普森激光科技有限公司 | Laser additive repair method for high-performance monocrystalline directional crystal turbine blade |
| CN112276086A (en) * | 2020-11-10 | 2021-01-29 | 西安交通大学 | Additive/equal-material preparation method for blade tenon |
| CN112276082A (en) * | 2020-10-15 | 2021-01-29 | 中国人民解放军第五七一九工厂 | Three-dimensional size repairing method for blade tips of compressed air rotor blades of aero-engine |
| CN114737185A (en) * | 2022-04-26 | 2022-07-12 | 西安交通大学 | Laser swing composite power modulation method for repairing single crystal turbine blade |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103074625A (en) * | 2013-01-16 | 2013-05-01 | 上海交通大学 | Movable laser cladding and repairing system |
| CN104480465A (en) * | 2014-12-24 | 2015-04-01 | 上海交通大学 | Method for manufacturing nickel-based monocrystal high-temperature alloy component by utilizing laser cladding technology |
| CN104694921A (en) * | 2015-03-18 | 2015-06-10 | 上海交通大学 | Method and device for controlling tissue growth in laser cladding of single crystal alloy |
| CN104831275A (en) * | 2015-05-09 | 2015-08-12 | 芜湖鼎瀚再制造技术有限公司 | Laser hot cladding process of blade |
-
2016
- 2016-02-25 CN CN201610102929.4A patent/CN105695986A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103074625A (en) * | 2013-01-16 | 2013-05-01 | 上海交通大学 | Movable laser cladding and repairing system |
| CN104480465A (en) * | 2014-12-24 | 2015-04-01 | 上海交通大学 | Method for manufacturing nickel-based monocrystal high-temperature alloy component by utilizing laser cladding technology |
| CN104694921A (en) * | 2015-03-18 | 2015-06-10 | 上海交通大学 | Method and device for controlling tissue growth in laser cladding of single crystal alloy |
| CN104831275A (en) * | 2015-05-09 | 2015-08-12 | 芜湖鼎瀚再制造技术有限公司 | Laser hot cladding process of blade |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106077647B (en) * | 2016-07-27 | 2018-04-06 | 湖南大学 | A kind of method that fragility Laves phases are controlled during laser gain material manufacture nickel base superalloy |
| CN106077647A (en) * | 2016-07-27 | 2016-11-09 | 湖南大学 | A kind of laser gain material controls the method for fragility Laves phase during manufacturing nickel base superalloy |
| CN108115249A (en) * | 2017-12-29 | 2018-06-05 | 西安交通大学 | A kind of system for repairing monocrystalline or orienting peritectic alloy blade |
| CN108213832A (en) * | 2017-12-29 | 2018-06-29 | 西安交通大学 | A kind of restorative procedure realized monocrystalline or orient peritectic alloy blade inner flow passage complex |
| CN110055526B (en) * | 2019-04-18 | 2021-01-08 | 江西省科学院应用物理研究所 | Energy-constrained laser epitaxial growth repair method for monocrystal superalloy |
| CN110055526A (en) * | 2019-04-18 | 2019-07-26 | 江西省科学院应用物理研究所 | A kind of single crystal super alloy laser epitaxial growth restorative procedure of energy constraint |
| CN111360251A (en) * | 2020-02-10 | 2020-07-03 | 中国科学院金属研究所 | Method for repairing single crystal high-temperature alloy thin-walled workpiece through powder feeding pulse laser 3D printing |
| CN111745160A (en) * | 2020-07-08 | 2020-10-09 | 哈尔滨工业大学 | Method for eliminating heat cracks in single crystal high-temperature alloy repair process under assistance of magnetic field |
| CN112122617A (en) * | 2020-08-21 | 2020-12-25 | 苏州华普森激光科技有限公司 | Laser additive repair method for high-performance monocrystalline directional crystal turbine blade |
| CN112276082A (en) * | 2020-10-15 | 2021-01-29 | 中国人民解放军第五七一九工厂 | Three-dimensional size repairing method for blade tips of compressed air rotor blades of aero-engine |
| CN112276086A (en) * | 2020-11-10 | 2021-01-29 | 西安交通大学 | Additive/equal-material preparation method for blade tenon |
| CN112276086B (en) * | 2020-11-10 | 2021-08-27 | 西安交通大学 | Additive/equal-material preparation method for blade tenon |
| CN114737185A (en) * | 2022-04-26 | 2022-07-12 | 西安交通大学 | Laser swing composite power modulation method for repairing single crystal turbine blade |
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Application publication date: 20160622 |