CN105671546B - A kind of active cooling device and cooling means of laser repairing single crystal turbine blade - Google Patents
A kind of active cooling device and cooling means of laser repairing single crystal turbine blade Download PDFInfo
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- CN105671546B CN105671546B CN201610102930.7A CN201610102930A CN105671546B CN 105671546 B CN105671546 B CN 105671546B CN 201610102930 A CN201610102930 A CN 201610102930A CN 105671546 B CN105671546 B CN 105671546B
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- cooling device
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- single crystal
- flow
- turbine blade
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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
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- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B11/00—Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method
- C30B11/003—Heating or cooling of the melt or the crystallised material
Abstract
The present invention proposes a kind of active cooling device and cooling means of laser repairing single crystal turbine blade, which includes：Air compressor, heat exchanger and ring type cooling device, gas compression to be cooled is high speed and high pressure air-flow by wherein described air compressor, and it is linked into the heat exchanger, the heat exchanger accesses ring type cooling device after accessing air-flow cooling, and the ring type cooling device is set to above the workbench of laser melting coating system and around workpiece setting.The active cooling device and cooling means proposed by the present invention for repairing single crystal turbine blade, by adjusting the size of cooling air-flow, the position of temperature and cooling nozzles and angle, makes to reach in laser repair process best active cooling effect.
Description
Technical field
The present invention relates to laser repairings and Fine Texture of Material to grow control field, and more particularly to a kind of reparation monocrystalline
The active cooling device and cooling means of turbo blade.
Background technology
Aero-engine plays the sufficient important role of act in modern Aviation industry.The performance indicator of aero-engine is direct
Decide the flying quality of aircraft.In recent decades, the development of aero-engine and aeronautical material, particularly heat-resisting material
Develop closely bound up.Crystal Nickel-based Superalloy has been widely used as the material of aero-engine Turbine Blades With temperature at present.Nickel
Based single-crystal high-temperature alloy causes the operating temperature of aero-engine from initial with its excellent high temperature and creep resistance, anti-fatigue performance
850 DEG C of increases are more than 1600 DEG C till now.Single crystal turbine blade high temperature, high pressure, pulsating stress load environment in it is long
Time service can generate various defects, such as the defects of fire check, abrasion, burn into crackle, material deficiency.These defects can reduce
The efficiency of aero-engine, it is serious aero-engine to be caused to damage.Nickel base single crystal high-temperature alloy material is expensive, monocrystalline
Turbo blade manufacturing process is complicated, and mortality is high.These factors lead to the price of every single crystal turbine blade up to 30,000 dollars.
Aero-engine maintenance cost can be reduced by extending the service life of single crystal turbine blade by recovery technique, save expensive material
Material, generates huge economic benefit.
Blade restorative procedure common at present includes arc-welding and laser melting coating.Renovation technique step mainly includes：Blade is clear
It washes, vane tip detection, crackle cleans and polishing, arc-welding or laser melting coating repairing, machining allowance and detection.Repairing this
In one link, arc-welding heat-source energy density is low, and heat input is big, can cause larger heat affected area.For single crystal turbine blade
Thin-walled tip structure, welding technology be difficult to only be molded repairs out new blade tip, and ensure repairing blade tip inside be and base material one
The single crystal organization of cause.Laser melting and coating process has many advantages, such as that heat-source energy density is big, heat input is small, can be molded over blade tip only
On repair out blade tip.Therefore laser melting and coating technique is current optimal single crystal turbine blade recovery technique.
The lattice of nickel-base high-temperature single crystal alloy is face-centered cubic, (micro- under certain temperature gradient with epitaxial growth characteristic
Seeing tissue can always grow along some crystal orientation).Laser melting coating monocrystal nickel-base high temperature closes in single crystal turbine blade tip surface
Jin Shi, with the solidification in molten bath, microstructure will be grown by epitaxial growth direction of the crystal orientation of single crystal blade blade tip.By molten
The influence of pond shape and temperature gradient, when single crystal organization grows into certain altitude, equiaxed grain structure will appear and prevent monocrystalline
Organize continued growth.In laser multilayer cladding process, equiaxed grain structure can block single crystal organization continuously to grow further up, and
And crystal boundary is generated between equiax crystal and single crystal organization.Since nickel-base high-temperature single crystal alloy lacks boundary-strengthening element.Once occur
Crystal boundary, under larger thermal stress, grain boundaries are easily cracked and extend extension along crystal boundary, directly affect reparation rear blade
Performance, it is difficult to meet the reparation requirement of single crystal blade.Therefore in the multilayer even leaf of multilayer multi-pass laser cladding reblading
During point, it is the key that ensure to obtain whole single crystal organizations in restoring area that equiaxed grain structure is fallen in complete remelting.
The distribution of single crystal organization is directly related to melting pool shape and temperature gradient, gentle molten bath and larger temperature gradient
Be conducive to the growth of single crystal organization.During laser repairing single crystal turbine blade tip, it is limited to the thin wall profile of vane tip, cladding
Heat in region is difficult to shed quickly through blade, caused by molten bath temperature gradient it is smaller.Therefore for laser repairing
For single crystal blade, compared to control melting pool shape, the temperature gradient in molten bath is controlled to be more prone to.By the temperature for increasing part
Gradient can enhance the epitaxial growth of single crystal organization, so as to reduce equiaxed grain structure, so as to fulfill isometric in multilayer cladding process
Crystalline substance tissue is remelted completely, meets the reparation requirement of single crystal turbine blade.
Invention content
The present invention proposes a kind of active cooling device and cooling means of laser repairing single crystal turbine blade, cold by adjusting
But the position of the size of air-flow, temperature and cooling nozzles and angle make to reach most during laser repairing single crystal turbine blade
Good active cooling effect.
In order to achieve the above object, the present invention proposes a kind of active cooling device of laser repairing single crystal turbine blade, packet
It includes：Air compressor, heat exchanger and ring type cooling device, wherein gas compression to be cooled is high at a high speed by the air compressor
Pressure gas stream, and be linked into the heat exchanger, the heat exchanger will access after air-flow cools down and access ring type cooling device, institute
Ring type cooling device is stated to be set to above the workbench of laser melting coating system and around workpiece setting.
Further, the gas to be cooled is argon gas, nitrogen or air.
Further, the flow of the high speed and high pressure air-flow is 10 liters/min -100 liters/min.
Further, the air pressure of the high speed and high pressure air-flow is 5 megapascal to 10 megapascal.
Further, the heat exchanger cooling material is liquid nitrogen, and access air-flow is cooled to -30 DEG C to -50 DEG C.
Further, the inner surface of the ring type cooling device is provided with solid matter aperture.
Further, the oblique lower angle of solid matter aperture is 10 ° to 80 ° ejection cooling air-flows.
In order to achieve the above object, the present invention also proposes the cooling side during a kind of laser repairing single crystal turbine blade
Method includes the following steps：
Gas to be cooled is formed into high speed and high pressure air-flow after air compressor；
High speed and high pressure air-flow is accessed into heat exchanger, heat exchange is carried out by pipeline back-shaped in heat exchanger, it is cold by air-flow is accessed
But ring type cooling device is accessed afterwards；
Cooling air-flow by the solid matter aperture of ring type cooling device inner surface is sprayed obliquely, one is formed around workpiece
A uniform annular coolant flow field.
Further, the flow of the high speed and high pressure air-flow is 10 liters/min -100 liters/min, and air pressure is 5 megapascal to 10
Megapascal.
Further, the heat exchanger cooling material is liquid nitrogen, and access air-flow is cooled to -30 DEG C to -50 DEG C.
Further, the oblique lower angle of the ring type cooling device inner surface solid matter aperture is sprayed for 10 ° to 80 ° cools down gas
Stream.
The present invention proposes a kind of active cooling device and cooling means of laser repairing single crystal turbine blade, by actively cold
But the outer wall of cladding peripheral region, particularly turbo blade can increase temperature gradient of the molten bath along vertical blade tip direction, so as to
Enhance the epitaxial growth ability of single crystal organization, reduce the generation of equiax crystal, realize company of the single crystal organization in multilayer cladding process
Continuous growth, so as to meet the spreading reparation requirement of single crystal blade blade tip abrasion.
Description of the drawings
Fig. 1 show the active cooling device structure diagram of the reparation single crystal turbine blade of present pre-ferred embodiments.
Fig. 2 show the ring type cooling device structure diagram of present pre-ferred embodiments.
Fig. 3 show the active cooling method flow diagram of the reparation single crystal turbine blade of present pre-ferred embodiments.
Fig. 4 show fine and closely woven continuous single crystal organization structure diagram in the single crystal blade after repairing.
Specific embodiment
The specific embodiment of the present invention is provided below in conjunction with attached drawing, but the present invention is not limited to following embodiments.Root
According to following explanation and claims, advantages and features of the invention will become apparent from.It should be noted that attached drawing is using very simple
The form of change and using non-accurate ratio, is only used for conveniently, lucidly aiding in illustrating the purpose of the embodiment of the present invention.
It please refers to Fig.1, Fig. 1 show the active cooling dress of the laser repairing single crystal turbine blade of present pre-ferred embodiments
Put structure diagram.The present invention proposes a kind of active cooling device of laser repairing single crystal turbine blade, including：Air compresses
Machine, heat exchanger and ring type cooling device, wherein gas compression to be cooled is high speed and high pressure air-flow by the air compressor, and will
It is linked into the heat exchanger, and the heat exchanger, which will be accessed after air-flow cools down, accesses ring type cooling device, the annular cooling
Device is set to above the workbench of laser melting coating system and around workpiece setting.
According to present pre-ferred embodiments, the gas to be cooled is argon gas, nitrogen or air.The high speed and high pressure air-flow
Flow be 10 liters/min -100 liters/min.The air pressure of the high speed and high pressure air-flow is 5 megapascal to 10 megapascal.The heat exchanger
Cooling material is liquid nitrogen, and access air-flow is cooled to -30 DEG C to -50 DEG C.
It please refers to Fig.2, Fig. 2 show the ring type cooling device structure diagram of present pre-ferred embodiments.The annular
The inner surface of cooling device 100 is provided with solid matter aperture 110.The solid matter that cooling air-flow passes through 100 inner surface of ring type cooling device
Aperture 110 sprays obliquely, and a uniformly annular coolant flow field is formed around blade.The angle that cooling air-flow sprays and annular
The angle of 100 inner surface solid matter aperture 110 of cooling device is related.100 inner surface solid matter aperture 110 of ring type cooling device is obliquely
Angle is 10 ° to 80 °.By adjusting the size of cooling air-flow, the position of temperature and cooling nozzles and angle, make laser repairing
Reach best active cooling effect in the process.
It please refers to Fig.3 again, Fig. 3 show the cooling means of the laser repairing single crystal turbine blade of present pre-ferred embodiments
Flow chart.The present invention also proposes a kind of active cooling method for repairing single crystal turbine blade, includes the following steps：
Step S100：Gas to be cooled is formed into high speed and high pressure air-flow after air compressor；
Step S200：High speed and high pressure air-flow is accessed into heat exchanger, heat exchange is carried out by pipeline back-shaped in heat exchanger, will connect
Ring type cooling device is accessed after entering air-flow cooling；
Step S300：Cooling air-flow is sprayed obliquely by the solid matter aperture of ring type cooling device inner surface, in workpiece
Surrounding forms a uniformly annular coolant flow field.
According to present pre-ferred embodiments, the flow of the high speed and high pressure air-flow is 10 liters/min -100 liters/min, gas
It presses as 5 megapascal to 10 megapascal.The heat exchanger cooling material is liquid nitrogen, and access air-flow is cooled to -30 DEG C to -50 DEG C.Institute
The oblique lower angle of ring type cooling device inner surface solid matter aperture is stated as 10 ° to 80 ° ejection cooling air-flows, one is formed around blade
A uniform annular coolant flow field.By adjusting the size of cooling air-flow, the position of temperature and cooling nozzles and angle, make laser
Reach best active cooling effect in repair process.
It please refers to Fig.4, Fig. 4 show fine and closely woven continuous single crystal organization structure diagram in the single crystal blade after repairing.This
Invention proposes a kind of active cooling device and cooling means of laser repairing single crystal turbine blade, around active cooling cladding
The outer wall in region, particularly turbo blade can increase temperature gradient of the molten bath along vertical blade tip direction, so as to enhance monocrystalline group
The epitaxial growth ability knitted reduces the generation of equiax crystal, realizes continuous growth of the single crystal organization in multilayer cladding process, so as to
Meet the spreading reparation requirement of single crystal blade blade tip abrasion.
In conclusion the present invention in original laser-processing system (including laser, powder feeder, mechanical arm, computer
With workbench etc.) on the basis of, add in blade ring type cooling device.It, will be cold during laser repairing single crystal turbine blade blade tip
But gas forms high speed and high pressure air-flow after air compressor, and accesses in heat exchanger.It is abundant by back-shaped pipeline and liquid nitrogen
After heat exchange, high-voltage high-speed airflow cooling air-flow in the ring type cooling device of blade, is cooled down by pipeline access ring by annular
The aperture of device inner surface sprays obliquely, the cooling gas flow field of annular is formed around blade, in turbine blade surface shape
Into active cooling area, so as to enhance the temperature gradient of blade axial direction.By the cooling gas flow and cooling tube that adjust vortex tube
Position and spray angle so that cooling effect reaches best.
Although the present invention is disclosed above with preferred embodiment, however, it is not to limit the invention.Skill belonging to the present invention
Has usually intellectual in art field, without departing from the spirit and scope of the present invention, when can be used for a variety of modifications and variations.Cause
This, the scope of protection of the present invention is defined by those of the claims.
Claims (10)
1. a kind of active cooling device for repairing single crystal turbine blade, which is characterized in that including：Air compressor, heat exchanger and
Ring type cooling device wherein gas compression to be cooled is high speed and high pressure air-flow by the air compressor, and is linked into institute
It states in heat exchanger, the heat exchanger will access after air-flow cools down and access ring type cooling device, the interior table of the ring type cooling device
Face is provided with solid matter aperture, and the ring type cooling device is set to above the workbench of laser melting coating system and is set around workpiece
It puts.
2. the active cooling device according to claim 1 for repairing single crystal turbine blade, which is characterized in that described to be cooled
Gas is argon gas, nitrogen or air.
3. the active cooling device according to claim 1 for repairing single crystal turbine blade, which is characterized in that the high speed is high
The flow of pressure gas stream is 10 liters/min -100 liters/min.
4. the active cooling device according to claim 1 for repairing single crystal turbine blade, which is characterized in that the high speed is high
The air pressure of pressure gas stream is 5 megapascal to 10 megapascal.
5. the active cooling device according to claim 1 for repairing single crystal turbine blade, which is characterized in that the heat exchanger
Cooling material is liquid nitrogen, and access air-flow is cooled to -30 DEG C to -50 DEG C.
6. the active cooling device according to claim 1 for repairing single crystal turbine blade, which is characterized in that the solid matter is small
Hole deviation downward angle is 10 ° to 80 ° ejection cooling air-flows.
A kind of 7. active cooling method for repairing single crystal turbine blade, which is characterized in that include the following steps：
Gas to be cooled is formed into high speed and high pressure air-flow after air compressor；
High speed and high pressure air-flow is accessed into heat exchanger, heat exchange is carried out by pipeline back-shaped in heat exchanger, after access air-flow cooling
Access ring type cooling device；
Cooling air-flow by the solid matter aperture of ring type cooling device inner surface is sprayed obliquely, one is formed around workpiece
Even annular coolant flow field.
8. the active cooling method according to claim 7 for repairing single crystal turbine blade, which is characterized in that the high speed is high
The flow of pressure gas stream is 10 liters/min -100 liters/min, and air pressure is 5 megapascal to 10 megapascal.
9. the active cooling method according to claim 7 for repairing single crystal turbine blade, which is characterized in that the heat exchanger
Cooling material is liquid nitrogen, and access air-flow is cooled to -30 DEG C to -50 DEG C.
10. the active cooling method according to claim 7 for repairing single crystal turbine blade, which is characterized in that the annular
The oblique lower angle of cooling device inner surface solid matter aperture is 10 ° to 80 ° ejection cooling air-flows.
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| CN201610102930.7A CN105671546B (en) | 2016-02-25 | 2016-02-25 | A kind of active cooling device and cooling means of laser repairing single crystal turbine blade |
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| CN201610102930.7A CN105671546B (en) | 2016-02-25 | 2016-02-25 | A kind of active cooling device and cooling means of laser repairing single crystal turbine blade |
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| CN105671546B true CN105671546B (en) | 2018-06-26 |
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| CN107576559A (en) * | 2017-10-11 | 2018-01-12 | 中国航发北京航空材料研究院 | A kind of cooling system for being used in high frequency fatigue test prevent sample overheat |
| CN107774997B (en) * | 2017-10-23 | 2021-02-05 | 江西瑞曼增材科技有限公司 | Laser directional material increase method for nickel-based directional superalloy |
| CN109702311A (en) * | 2019-03-06 | 2019-05-03 | 南昌航空大学 | A kind of electron beam fuse restorative procedure of single crystal super alloy |
| CN109822192B (en) * | 2019-03-06 | 2023-10-03 | 南昌航空大学 | Preparation method of single crystal intermediate layer of single crystal superalloy |
| US11371349B2 (en) * | 2019-04-05 | 2022-06-28 | Raytheon Technologies Corporation | Gas impingement in-process cooling system |
| 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 |
| CN116219434B (en) * | 2023-05-04 | 2023-07-07 | 成都裕鸢航空智能制造股份有限公司 | Repair device and repair method for turbine guide vane of aero-engine |
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