CN106591826A - Repair material for repairing turbine blade tip cracks and repair method thereof - Google Patents
Repair material for repairing turbine blade tip cracks and repair method thereof Download PDFInfo
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- CN106591826A CN106591826A CN201610955034.5A CN201610955034A CN106591826A CN 106591826 A CN106591826 A CN 106591826A CN 201610955034 A CN201610955034 A CN 201610955034A CN 106591826 A CN106591826 A CN 106591826A
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- blade tip
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- repair
- turbo
- restorative procedure
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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
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
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- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention relates to the technical field of maintenance of aviation engines, in particular to a repair material for repairing turbine blade tip cracks and a repair method thereof. The repair material is high-strength oxidation resisting nickel base high-temperature alloy powder; an inert atmosphere induction preheating laser cladding technology is adopted to repair deep crack parts at blade tips of high-pressure turbine working blades; the high-pressure turbine working blades adopt the materials of directional solidification nickel base high-temperature alloys DZ125; and the repair process comprises coating layer removal-polishing of blade tip deep cracks-repair path planning-inert atmosphere induction preheating-laser cladding-shape finishing by manual polishing-coating layer recovery. The repair material realizes repair of directional solidification high-pressure turbine working blades with cracks extending to a cover plate; the cracks are not discovered by the X-ray and fluorescent penetrant inspection after repair; a repair interface has an oriented crystal structure; the life of the repaired high-pressure turbine working blades can reach above 380 hours; and the repair material has important significance on acceleration of application and development of the aviation technology.
Description
Technical field
The present invention relates to aircraft engine maintenance technical field, and in particular to one kind is used for repairing turbine blade tip crackle
Repair materials and its restorative procedure.
Background technology
Certain type aero-engine high-pressure turbine working blade is using the accurate casting of nickel base superalloy DZ125 directional solidifications crystallization
Make and form.At work there is substantial amounts of longitudinal crack to high-pressure turbine working blade in blade tip after one overhaul life, and research shows
High-pressure turbine working blade blade tip deep torn grain is mainly heat fatigue cracking, and most of crackle has been split to cover plate, for up to 4
Mm, belongs to deep torn grain category.DZ125 is high alumina, the high temperature alloy of titanium（The percentage by weight of Al+Ti contents is about 8 %）, and be
Blade is that directional solidification crystallization hot investment casting is formed, readily along fixed during the conventional method repairing such as argon arc weld deposit compound leaf point deep torn grain
New crackle is produced to solidification and crystallization direction, this is not concentrated mainly due to conventional argon arc welding energy, heat affected area is big, high
Aluminum, Ti content cause second easily to separate out in welding and cause to mismatch with matrix thermal coefficient of expansion and produce micro-crack.
At present the country does not also disclose report with regard to the deep-fissured restorative procedure of directional solidification high-pressure turbine working blade blade tip.
The content of the invention
It is an object of the invention to solve above technical problem, there is provided a kind of repairing for repairing turbine blade tip crackle
Multiple material and its restorative procedure, using inert atmosphere sensing preheating laser melting and coating technique high-pressure turbine working blade blade tip depth is repaired
Crack site, high-pressure turbine working blade material is directional solidification nickel-base high-temperature alloy DZ125；Repairing flow process is：Remove removing coating
→ blade tip deep torn grain polishing → repair path planning → inert atmosphere sensing preheating → laser melting coating → manual grinding repair external form →
Recover coating.
To solve the above problems, the present invention is employed the following technical solutions：
A kind of repair materials for repairing turbine blade tip crackle, the repair materials are high-strength, antioxidant nickel-base high-temperature
Alloy powder, is made up of by percentage to the quality following components：Chromium 8.6-10%, cobalt 13-15%, carbon 0.2-0.25%, molybdenum 2.3-
2.7%, tungsten 3.4-4.1%, aluminum 6-6.3%, tantalum 5.2-6.2%, zirconium 0.03-0.05, boron 0.02-0.05%, rhenium 1.6-2%, hafnium 1.5-
2.7%, balance of nickel.
Further, the particle diameter of the high-strength, antioxidant Ni-base Superalloy Powder is -100 ~+325 mesh.
A kind of restorative procedure of turbo blade blade tip crackle, comprises the following steps：
S1. cleaning removes turbine blade surface coating；
S2. turbo blade is processed by mechanical grinding, turbo blade blade tip slit region is polished into into V-groove；
S3. turbo blade blade tip is preheated by inert atmosphere high-frequency induction, preheating temperature is 900-1000 DEG C；
S4. repair materials are successively piled up along turbo blade blade tip direction of check using laser melting coating, the work of the laser melting coating
Skill parameter is：Scanning speed is 3-4mm/s, and laser power is 130-230W, and laser spot diameter is 1mm, powder feeding rate 2-3g/
min；
S5. and then polishing reparation, applying coating are carried out to blade tip.
Further, the another kind of of step S1 selects to be to remove turbine blade surface coating by mechanical grinding.
Further, step S1 is using Chemical cleaning and mechanical grinding combined removal turbine blade surface coating.
Further, in step S2, the opening angle of V-groove is 50-70 °.
Further, in step S3, water, oxygen, the content of nitrogen are respectively smaller than 10ppm in inert atmosphere.
Further, in step S3, inert atmosphere high-frequency induction pair is completed using profiling copper alloy hollow pipe
The operation that turbo blade blade tip is preheated, the profiling copper alloy hollow pipe inside leads to cooling water, profiling copper alloy hollow pipe
Copper coil is provided with, copper coil is 3-5mm away from blade distance, and sensed position is bucket cover plate region.
Further, in step S4, using laser melting coating by cladding material along turbo blade blade tip direction of check by
Layer is piled up, and monolayer is highly 0.8mm.
Further, in step S4, the molten path of covering of blade tip V-groove is adopted on the thickness direction of turbo blade
Cover to blade back from leaf basin molten, short path is successively piled up, be then successively accumulated to blade tip height further along blade tip direction of check.
Further, described per layer covers molten laser optical cable and successively decreases successively from the bottom up 20W.
Further, in step S5, polishing reparation is carried out to blade tip by manual grinding.
Further, in step S5, using vacuum arc plating or electro beam physics vapour deposition technology applying coating.
Further, the turbo blade is aero-engine high-pressure turbine blade.
A kind of repair materials and its restorative procedure for repairing turbine blade tip crackle of the present invention, with prior art phase
Than, its protrusion the characteristics of and excellent effect be：The bright directional solidification high-pressure turbine work for realizing crack growth to cover plate of this law
Make the reparation of blade, X-ray and fluorescent penetrating inspection after reparation does not find crackle, repair interface and there is the brilliant tissue of orientation, the height after reparation
The pressure moving turbine blade life-span can reach more than 380 hours, be widely used in aero-engine high-pressure turbine working blade orientation
The reparation of solidification nickel base superalloy DZ125, the application development to promoting aeronautical technology is significant.
Description of the drawings
Fig. 1 is schematic diagram before the polishing of the turbo blade blade tip of experimental example 4；
Fig. 2 is schematic diagram after the turbo blade blade tip of experimental example 4 polishing section；
Fig. 3 is schematic diagram after the turbo blade of experimental example 4 polishing crackle；
Fig. 4 is the structural representation of copper coil；
In figure, 1 is blade, and 2 is cover plate, and 3 is boss, and 4 is crackle, and 5 is V-groove.
Specific embodiment
Below by way of specific embodiment and accompanying drawing, the present invention is described in further detail, but should not be interpreted as this
The scope of the present invention is only limitted to Examples below.It is general according to this area in the case of without departing from said method thought of the present invention
Various replacements or change that logical technological know-how and customary means are made, should be included in the scope of the present invention.
Embodiment 1
A kind of repair materials for repairing turbine blade tip crackle, are high-strength, antioxidant Ni-base Superalloy Powder, by
Following components is constituted by percentage to the quality：Chromium 8.6%, cobalt 15%, carbon 0.25%, molybdenum 2.3%, tungsten 3.4%, aluminum 6.1%, tantalum 5.4%,
Zirconium 0.03, boron 0.05%, rhenium 1.6%, hafnium 1.5%, balance of nickel.
Embodiment 2
A kind of repair materials for repairing turbine blade tip crackle, are high-strength, antioxidant Ni-base Superalloy Powder, by
Following components is constituted by percentage to the quality：Chromium 10%, cobalt 13%, carbon 0.2%, molybdenum 2.7%, tungsten 4.1%, aluminum 6%, tantalum 6.2%, zirconium
0.05, boron 0.02%, rhenium 2%, hafnium 2.7%, balance of nickel.
Embodiment 3
A kind of repair materials for repairing turbine blade tip crackle, are high-strength, antioxidant Ni-base Superalloy Powder, powder
Last granularity is -100 ~+325 mesh, is made up of by percentage to the quality following components：Chromium 9%, cobalt 14%, carbon 0.22%, molybdenum 2.5%, tungsten
4%, aluminum 6.2%, tantalum 6%, zirconium 0.04, boron 0.03%, rhenium 1.8%, hafnium 2%, balance of nickel.
Embodiment 4
A kind of repair materials for repairing turbine blade tip crackle, are high-strength, antioxidant Ni-base Superalloy Powder, powder
Last granularity is -100 ~+325 mesh, is made up of by percentage to the quality following components：Chromium 9%, cobalt 14%, carbon 0.22%, molybdenum 2.5%, tungsten
4%, aluminum 6.3%, tantalum 5.2%, zirconium 0.04, boron 0.03%, rhenium 1.8%, hafnium 2.1%, balance of nickel.
Experimental example 1
A kind of restorative procedure of turbo blade blade tip crackle, using the repair materials described in embodiment 3, comprises the following steps：
S1. cleaning removes turbine blade surface coating；
S2. turbo blade is processed by mechanical grinding, turbo blade blade tip slit region is polished into into V-groove；
S3. turbo blade blade tip is preheated by inert atmosphere high-frequency induction, preheating temperature is 900 DEG C；
S4. repair materials are successively piled up along turbo blade blade tip direction of check using laser melting coating, the work of the laser melting coating
Skill parameter is：Scanning speed is 3mm/s, and laser power is 130-230W, and laser spot diameter is 1mm, powder feeding rate 3g/min；
S5. and then polishing reparation, applying coating are carried out to blade tip.
Experimental example 2
A kind of restorative procedure of turbo blade blade tip crackle, using repairing described in the repair materials described in embodiment 3 and experimental example 1
The preheating temperature of compound recipe method, wherein step S3 is 1000 DEG C, and the technological parameter of laser melting coating is in step S4：Scanning speed is
4mm/s, laser power is 130-230W, and laser spot diameter is 1mm, powder feeding rate 2g/min.
Experimental example 3
A kind of restorative procedure of turbo blade blade tip crackle, using repairing described in the repair materials described in embodiment 3 and experimental example 1
The preheating temperature of compound recipe method, wherein step S3 is 950 DEG C, and the technological parameter of laser melting coating is in step S4：Scanning speed is
3.5mm/s, laser power is 130-230W, and laser spot diameter is 1mm, powder feeding rate 2.5g/min.
Experimental example 4
A kind of restorative procedure of turbo blade blade tip crackle, blade tip deep torn grain occurs in leaf pelvic part position, and length is 4 mm, using this
The method that invention is provided is repaired, and is repaired flow process and is：Go removing coating → blade tip deep torn grain polishing → repair path planning → lazy
Property atmosphere sensing preheating → laser melting coating → manual grinding repair external form → recovery coating.High pressure whirlpool is removed initially with chemical method
Whole coatings on wheel working-blade surface, the remaining coating to removing is removed using the method for mechanical grinding.Then adopt
The method polishing high-pressure turbine working blade blade tip deep torn grain of mechanical grinding, whole end face of first polishing is to land area, Ran Hou
Slit region is polished into v-shaped openings, and angle is 60 °, polishing schematic diagram as shown in Figure 1, Figure 2 and Figure 3.In path planning side
Face, the cladding path of v-shaped openings is adopted on the thickness direction of high-pressure turbine working blade from leaf basin to the side of blade back cladding
Formula, short path is successively piled up, and successively piles up high with the blade tip required for reaching further along blade tip type face after v-shaped openings cladding is complete
Degree；Material used in cladding is the repair materials described in embodiment 3.With the mode of inert atmosphere high-frequency induction preheating before cladding
Blade tip is preheated, using profiling copper alloy hollow pipe（As shown in Figure 2）, the logical cooling water in inside, copper coil is apart from blade week
4 mm are enclosed, sensed position is Panel area, and preheating temperature is 950 DEG C, and the water, oxygen, the content of nitrogen in inert atmosphere is 5
ppm.The technological parameter of laser melting coating is：Scanning speed be 3 mm/s, laser power be 130 ~ 230W, laser spot diameter 1.0
Mm, powder feeding rate be 2 g/min, monolayer height 0.8 mm, overlapping rate 50%.The power of every layer of cladding successively decreases successively from the bottom up 20
W.Finally profiling polishing is carried out to the high-pressure turbine working blade blade tip external form repaired using manual grinding method.Cladding layer and base
Material rounding off, high-pressure turbine working blade highly meets design requirement.It is heavy using vacuum arc plating or electron beam physical vapor
Product technology applying coating again.X-ray and fluorescent penetrating inspection after reparation does not find crackle, repairs interface and has the brilliant tissue of orientation, repairs
The high-pressure turbine working blade life-span afterwards can reach more than 380 hours.
Experimental example 5
A kind of restorative procedure of turbo blade blade tip crackle, blade tip deep torn grain occurs in blade back position, and length is 4 mm, repairs stream
Cheng Wei：Go removing coating → blade tip deep torn grain polishing → repair path planning → inert atmosphere sensing preheating → laser melting coating → craft
External form → recovery coating is repaiied in polishing.Whole coatings on high-pressure turbine working blade surface are removed initially with chemical method, to nothing
The remaining coating that method is removed is removed using the method for mechanical grinding.Then using the method polishing high-pressure turbine working of mechanical grinding
Then blade tip deep torn grain, whole end face of first polishing is polished into v-shaped openings to land area in slit region, and angle is
70°.In terms of path planning, the cladding path of v-shaped openings is adopted on the thickness direction of high-pressure turbine working blade from leaf
Basin to the mode of blade back cladding, successively pile up, successively pile up to reach further along blade tip type face after v-shaped openings cladding is complete by short path
To required blade tip height.The mode preheated with inert atmosphere high-frequency induction before cladding is preheated to blade tip, using profiling
Copper alloy hollow pipe, the logical cooling water in inside, copper coil 4 mm around blade, sensed position is Panel area, preheating temperature
For 1000 DEG C, the water, oxygen, the content of nitrogen in inert atmosphere is 3 ppm.Material used in cladding is superhigh intensity antioxidation
Ni-base Superalloy Powder, the powder using argon atomization method prepare, powder size be -100 ~+325 mesh, powder chemistry into
Point（Percentage by weight）For：Nickel：Surplus, chromium：9.00%, cobalt：14.00%, carbon：0.22%, molybdenum：2.50%, tungsten：4.00%, aluminum：
6.20%, tantalum：6.00%, zirconium：0.04%, boron：0.03%, rhenium：1.80%, hafnium：2.00%.The technological parameter of laser melting coating is：Scanning
Speed：4 mm/s, laser power：130 ~ 230W, the mm of processing stand spot diameter 1.0, powder feeding rate：3 g/min, monolayer height 0.8
Mm, overlapping rate 50%.The power of every layer of cladding successively decreases successively from the bottom up 20 W.Finally using manual grinding method to reparation
High-pressure turbine working blade blade tip external form carries out profiling polishing.Cladding layer and base material rounding off, high-pressure turbine working blade is high
Degree meets design requirement.Using vacuum arc plating or electro beam physics vapour deposition technology again applying coating.After reparation X-ray and
Fluorescent penetrating inspection does not find crackle, repairs interface and has the brilliant tissue of orientation, and the high-pressure turbine working blade life-span after reparation can reach
More than 380 hours.
Claims (10)
1. a kind of repair materials for repairing turbine blade tip crackle, it is characterised in that the repair materials are high intensity
Antioxidation Ni-base Superalloy Powder, is made up of by percentage to the quality following components：Chromium 8.6-10%, cobalt 13-15%, carbon 0.2-
0.25%, molybdenum 2.3-2.7%, tungsten 3.4-4.1%, aluminum 6-6.3%, tantalum 5.2-6.2%, zirconium 0.03-0.05, boron 0.02-0.05%, rhenium
1.6-2%, hafnium 1.5-2.7%, balance of nickel.
2. a kind of repair materials for repairing turbine blade tip crackle according to claim 1, it is characterised in that institute
The particle diameter for stating high-strength, antioxidant Ni-base Superalloy Powder is -100 ~+325 mesh.
3. a kind of restorative procedure of turbo blade blade tip crackle, it is characterised in that comprise the following steps：
S1. cleaning removes turbine blade surface coating；
S2. turbo blade is processed by mechanical grinding, turbo blade blade tip slit region is polished into into V-groove；
S3. turbo blade blade tip is preheated by inert atmosphere high-frequency induction, preheating temperature is 900-1000 DEG C；
S4. repair materials are successively piled up along turbo blade blade tip direction of check using laser melting coating, the work of the laser melting coating
Skill parameter is：Scanning speed is 3-4mm/s, and laser power is 130-230W, and laser spot diameter is 1mm, powder feeding rate 2-3g/
min；
S5. and then polishing reparation, applying coating are carried out to blade tip.
4. a kind of restorative procedure of turbo blade blade tip crackle according to claim 3, it is characterised in that step S1
Another kind of select to be to remove turbine blade surface coating by mechanical grinding.
5. a kind of restorative procedure of turbo blade blade tip crackle according to claim 3, it is characterised in that step S2
In, the opening angle of V-groove is 50-70 °.
6. a kind of restorative procedure of turbo blade blade tip crackle according to claim 3, it is characterised in that step S3
In, water, oxygen, the content of nitrogen are respectively smaller than 10ppm in inert atmosphere.
7. a kind of restorative procedure of turbo blade blade tip crackle according to claim 3, it is characterised in that step S4
In, cladding material successively to be piled up along turbo blade blade tip direction of check using laser melting coating, monolayer is highly 0.8mm.
8. the restorative procedure of a kind of turbo blade blade tip crackle according to claim 7, it is characterised in that described per layer covers
Molten laser optical cable successively decreases successively from the bottom up 20W.
9. a kind of restorative procedure of turbo blade blade tip crackle according to claim 3, it is characterised in that step S5
In, polishing reparation is carried out to blade tip by manual grinding.
10. a kind of restorative procedure of turbo blade blade tip crackle according to claim 3, it is characterised in that the step
In S5, using vacuum arc plating or electro beam physics vapour deposition technology applying coating.
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| CN110480007A (en) * | 2019-05-23 | 2019-11-22 | 中国人民解放军第五七一九工厂 | A kind of micro- high-intensitive wound restorative procedure of the aero-engine without hat directional solidification crystalline substance moving turbine blade blade tip crackle |
| CN111850546A (en) * | 2020-06-28 | 2020-10-30 | 华中科技大学 | Method for repairing nickel-aluminum bronze part through laser cladding and product thereof |
| CN112045363A (en) * | 2020-08-07 | 2020-12-08 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN112139495A (en) * | 2020-09-01 | 2020-12-29 | 大连理工大学 | Method for repairing broken teeth of gear through additive remanufacturing |
| 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 |
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| CN109261965A (en) * | 2018-11-09 | 2019-01-25 | 成都青石激光科技有限公司 | A kind of plugging technology of turbine buckets of gas turbine piece cover board apical pore |
| CN110480007A (en) * | 2019-05-23 | 2019-11-22 | 中国人民解放军第五七一九工厂 | A kind of micro- high-intensitive wound restorative procedure of the aero-engine without hat directional solidification crystalline substance moving turbine blade blade tip crackle |
| CN111850546A (en) * | 2020-06-28 | 2020-10-30 | 华中科技大学 | Method for repairing nickel-aluminum bronze part through laser cladding and product thereof |
| CN112045363B (en) * | 2020-08-07 | 2022-03-11 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN112045363A (en) * | 2020-08-07 | 2020-12-08 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN112139495A (en) * | 2020-09-01 | 2020-12-29 | 大连理工大学 | Method for repairing broken teeth of gear through additive remanufacturing |
| 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 |
| CN112427637A (en) * | 2020-11-20 | 2021-03-02 | 中国人民解放军第五七一九工厂 | Repair material and repair method for deep cracks of blade tips of directionally solidified crystal turbine blades |
| CN112427637B (en) * | 2020-11-20 | 2023-01-20 | 中国人民解放军第五七一九工厂 | Repair material and repair method for deep cracks of blade tips of directionally solidified crystal turbine blades |
| CN113337756A (en) * | 2021-06-02 | 2021-09-03 | 西安空天机电智能制造有限公司 | Nickel-based superalloy repair material and preparation method thereof |
| CN113337756B (en) * | 2021-06-02 | 2022-05-24 | 西安空天机电智能制造有限公司 | Nickel-based superalloy repair material and preparation method thereof |
| CN115740950A (en) * | 2022-11-01 | 2023-03-07 | 中国航发沈阳黎明航空发动机有限责任公司 | DZ125 alloy based on reverse modeling turbine blade laser deposition repair method |
| CN115740950B (en) * | 2022-11-01 | 2024-05-03 | 中国航发沈阳黎明航空发动机有限责任公司 | DZ125 alloy turbine blade laser deposition repair method based on reverse modeling |
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