CN106591826B - A kind of repair materials and its restorative procedure for repairing turbine blade tip crackle - Google Patents
A kind of repair materials and its restorative procedure for repairing turbine blade tip crackle Download PDFInfo
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- CN106591826B CN106591826B CN201610955034.5A CN201610955034A CN106591826B CN 106591826 B CN106591826 B CN 106591826B CN 201610955034 A CN201610955034 A CN 201610955034A CN 106591826 B CN106591826 B CN 106591826B
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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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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to aircraft engine maintenance technical fields, more particularly to a kind of repair materials and its restorative procedure for repairing turbine blade tip crackle, the repair materials are high-strength, antioxidant Ni-base Superalloy Powder, preheating laser melting and coating technique is incuded using inert atmosphere and repairs high-pressure turbine working blade blade tip deep torn grain position, high-pressure turbine working blade material is directional solidification nickel-base high-temperature alloy DZ125；Repair process are as follows: removing coating → blade tip deep torn grain polishing → repair path planning → inert atmosphere induction preheating → laser melting coating → manual grinding is gone to repair external form → recovery coating.The present invention realize crack growth to cover board directional solidification high-pressure turbine working blade reparation, X-ray and fluorescent penetrating inspection do not find crackle after reparation, repairing interface has the brilliant tissue of orientation, the high-pressure turbine working blade service life after reparation can reach 380 hours or more, be of great significance to the application development for promoting aeronautical technology.
Description
Technical field
The present invention relates to aircraft engine maintenance technical fields, and in particular to one kind is used for repairing turbine blade tip crackle
Repair materials and its restorative procedure.
Background technique
Certain type aero-engine high-pressure turbine working blade is using the accurate casting of nickel base superalloy DZ125 directional solidification crystallization
It makes.There is a large amount of longitudinal crack to high-pressure turbine working blade in blade tip at work after one overhaul life, research shows that
High-pressure turbine working blade blade tip deep torn grain is mainly heat fatigue cracking, and most of crackle has been split to cover board, and longest reaches 4
Mm belongs to deep torn grain scope.DZ125 is the high temperature alloy (weight percent of Al+Ti content is about 8 %) of high alumina, titanium, and is
Blade is that directional solidification crystallization hot investment casting forms, and the conventional methods such as argon arc weld deposit are when repairing blade tip deep torn grain readily along fixed
New crackle is generated to solidification and crystallization direction, this is mainly due to conventional argon arc welding energy not to concentrate, and heat affected area is big, high
Aluminium, Ti content make the second phase be easy to be precipitated and cause to mismatch with matrix thermal expansion coefficient and generate micro-crack in welding.
Restorative procedure of the report open not yet domestic at present about directional solidification high-pressure turbine working blade blade tip deep torn grain.
Summary of the invention
It is an object of the invention to solve the above technical problem, a kind of repairing for repairing turbine blade tip crackle is provided
Multiple material and its restorative procedure incude preheating laser melting and coating technique using inert atmosphere and repair high-pressure turbine working blade blade tip depth
Crack site, high-pressure turbine working blade material are directional solidification nickel-base high-temperature alloy DZ125；Repair process are as follows: remove removing coating
→ blade tip deep torn grain polishing → repair path planning → inert atmosphere induction preheating → laser melting coating → manual grinding repair external form →
Restore coating.
To solve the above problems, the invention adopts the following technical scheme:
A kind of repair materials for repairing turbine blade tip crackle, the repair materials are that high-strength, antioxidant is Ni-based
Superalloy powder is made 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%, aluminium 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%, surplus are nickel.
Further, the partial size of the high-strength, antioxidant Ni-base Superalloy Powder is -100 ~+325 mesh.
A kind of restorative procedure of turbo blade blade tip crackle, comprising the following steps:
S1. cleaning removal turbine blade surface coating；
S2. turbo blade is handled by mechanical grinding, turbo blade blade tip slit region is polished 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 accumulated along turbo blade blade tip direction of check using laser melting coating, the laser melting coating
Technological parameter are as follows: scanning speed 3-4mm/s, laser power 130-230W, laser spot diameter 1mm, powder feeding rate 2-
3g/min；
S5. polishing reparation, applying coating then are carried out to blade tip.
Further, the another kind of the step S1, which is selected as, removes turbine blade surface coating by mechanical grinding.
Further, the step S1 is using chemical cleaning and mechanical grinding combined removal turbine blade surface coating.
Further, in the step S2, the opening angle of V-groove is 50-70 °.
Further, in the step S3, water in inert atmosphere, oxygen, nitrogen content be respectively smaller than 10ppm.
Further, in the 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 lead to cooling water, profiling copper alloy hollow pipe
It is equipped with copper coil, copper coil is 3-5mm away from blade distance, and sensed position is bucket cover plate region.
Further, in the step S4, using laser melting coating by cladding material along turbo blade blade tip direction of check by
Layer heap product, single layer height are 0.8mm.
Further, in the step S4, the molten path of covering of blade tip V-groove is used on the thickness direction of turbo blade
Covered from leaf basin to blade back molten, short path is successively accumulated, and is then successively accumulated to blade tip height further along blade tip direction of check.
Further, the laser power of every layer of cladding is successively successively decreased 20W from the bottom up.
Further, in the step S5, polishing reparation is carried out to blade tip by manual grinding.
Further, in the 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 the feature and excellent effect protruded is: the bright directional solidification high-pressure turbine work for realizing crack growth to cover board of this law
Make the reparation of blade, X-ray and fluorescent penetrating inspection do not find crackle after reparation, and repairing interface has the brilliant tissue of orientation, the height after reparation
The pressure moving turbine blade service life can reach 380 hours or more, be widely used in aero-engine high-pressure turbine working blade orientation
The reparation for solidifying nickel base superalloy DZ125 is of great significance to the application development for promoting aeronautical technology.
Detailed description of the invention
Fig. 1 is schematic diagram before 4 turbo blade blade tip of experimental example is polished；
Fig. 2 is schematic diagram after 4 turbo blade blade tip of experimental example polishing section；
Fig. 3 is schematic diagram after 4 turbo blade of experimental example polishing crackle；
Fig. 4 is the structural schematic diagram of copper coil；
In figure, 1 is blade, and 2 be cover board, and 3 be boss, and 4 be crackle, and 5 be V-groove.
Specific embodiment
Below by way of specific embodiment and attached 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 example below.Without departing from the idea of the above method of the present invention, general according to this field
The 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 nickel base superalloy powder
End is made of by percentage to the quality following components: chromium 8.6%, cobalt 15%, carbon 0.25%, molybdenum 2.3%, tungsten 3.4%, aluminium 6.1%, tantalum
5.4%, zirconium 0.03%, boron 0.05%, rhenium 1.6%, hafnium 1.5%, surplus is nickel.
Embodiment 2
A kind of repair materials for repairing turbine blade tip crackle are high-strength, antioxidant nickel base superalloy powder
End is made of by percentage to the quality following components: chromium 10%, cobalt 13%, carbon 0.2%, molybdenum 2.7%, tungsten 4.1%, aluminium 6%, tantalum 6.2%,
Zirconium 0.05%, boron 0.02%, rhenium 2%, hafnium 2.7%, surplus are nickel.
Embodiment 3
A kind of repair materials for repairing turbine blade tip crackle are high-strength, antioxidant nickel base superalloy powder
End, powder size are -100 ~+325 mesh, are made of by percentage to the quality following components: chromium 9%, cobalt 14%, carbon 0.22%, molybdenum
2.5%, tungsten 4%, aluminium 6.2%, tantalum 6%, zirconium 0.04%, boron 0.03%, rhenium 1.8%, hafnium 2%, surplus is nickel.
Embodiment 4
A kind of repair materials for repairing turbine blade tip crackle are high-strength, antioxidant nickel base superalloy powder
End, powder size are -100 ~+325 mesh, are made of by percentage to the quality following components: chromium 9%, cobalt 14%, carbon 0.22%, molybdenum
2.5%, tungsten 4%, aluminium 6.3%, tantalum 5.2%, zirconium 0.04%, boron 0.03%, rhenium 1.8%, hafnium 2.1%, surplus is nickel.
Experimental example 1
A kind of restorative procedure of turbo blade blade tip crackle, using repair materials described in embodiment 3, including following step
It is rapid:
S1. cleaning removal turbine blade surface coating；
S2. turbo blade is handled by mechanical grinding, turbo blade blade tip slit region is polished 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 accumulated along turbo blade blade tip direction of check using laser melting coating, the laser melting coating
Technological parameter are as follows: scanning speed 3mm/s, laser power 130-230W, laser spot diameter 1mm, powder feeding rate 3g/
min；
S5. polishing reparation, applying coating then are carried out to blade tip.
Experimental example 2
A kind of restorative procedure of turbo blade blade tip crackle, using described in repair materials described in embodiment 3 and experimental example 1
Restorative procedure, wherein the preheating temperature of step S3 is 1000 DEG C, the technological parameter of laser melting coating in step S4 are as follows: scanning speed
For 4mm/s, laser power 130-230W, laser spot diameter 1mm, powder feeding rate 2g/min.
Experimental example 3
A kind of restorative procedure of turbo blade blade tip crackle, using described in repair materials described in embodiment 3 and experimental example 1
Restorative procedure, wherein the preheating temperature of step S3 is 950 DEG C, the technological parameter of laser melting coating in step S4 are as follows: scanning speed
For 3.5mm/s, laser power 130-230W, laser spot diameter 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 appear in leaf pelvic part position, and length is 4 mm, adopt
It is repaired with method provided by the invention, repairs process are as follows: go removing coating → blade tip deep torn grain polishing → repair path planning
→ inert atmosphere induction preheating → laser melting coating → manual grinding repairs external form → recovery coating.It is high using chemical method removal first
The whole coatings for pressing moving turbine blade surface remove the remaining coating that do not can be removed using the method for mechanical grinding.Then
It is polished high-pressure turbine working blade blade tip deep torn grain using the method for mechanical grinding, entire end face of first polishing is to land area, so
Be polished into v-shaped openings in slit region afterwards, angle is 60 °, polishing schematic diagram.In path planning
Aspect, the cladding paths of v-shaped openings use on the thickness direction of high-pressure turbine working blade from leaf basin to blade back cladding
Mode, short path are successively accumulated, and are successively accumulated further along blade tip type face to reach required blade tip after v-shaped openings cladding is complete
Highly；Material used in cladding is repair materials described in embodiment 3.The side preheated before cladding with inert atmosphere high-frequency induction
Formula preheats blade tip, and using profiling copper alloy hollow pipe (as shown in Figure 2), the logical cooling water in inside, copper coil is apart from blade
4 mm of surrounding, sensed position are Panel area, and preheating temperature is 950 DEG C, and the content of water, oxygen, nitrogen in inert atmosphere is 5
ppm.The technological parameter of laser melting coating are as follows: scanning speed is 3 mm/s, and laser power is 130 ~ 230W, laser spot diameter 1.0
Mm, powder feeding rate are 2 g/min, 0.8 mm of single layer height, overlapping rate 50%.The power of every layer of cladding successively successively decreases 20 from the bottom up
W.Profiling polishing is finally carried out using high-pressure turbine working blade blade tip external form of the manual grinding method to reparation.Cladding layer and base
Material rounding off, high-pressure turbine working blade height meet 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 do not find crackle after reparation, and repairing interface has the brilliant tissue of orientation, repair
The high-pressure turbine working blade service life afterwards can reach 380 hours or more.
Experimental example 5
A kind of restorative procedure of turbo blade blade tip crackle, blade tip deep torn grain appear in blade back position, and length is 4 mm, repair
Resurgent journey are as follows: go removing coating → blade tip deep torn grain polishing → repair path planning → inert atmosphere induction preheating → laser melting coating →
Manual grinding repairs external form → recovery coating.Whole coatings on high-pressure turbine working blade surface are removed using chemical method first,
The remaining coating that do not can be removed is removed using the method for mechanical grinding.Then using the method polishing high-pressure turbine of mechanical grinding
Then working-blade blade tip deep torn grain, entire end face of first polishing are polished into v-shaped openings, angle in slit region to land area
Degree is 70 °.In terms of path planning, the cladding path of v-shaped openings is used on the thickness direction of high-pressure turbine working blade
From leaf basin to the mode of blade back cladding, short path is successively accumulated, and is successively accumulated after v-shaped openings cladding is complete further along blade tip type face
To reach required blade tip height.Blade tip is preheated with the mode that inert atmosphere high-frequency induction preheats before cladding, is used
Profiling copper alloy hollow pipe, the logical cooling water in inside, copper coil 4 mm around blade, sensed position is Panel area, preheating
Temperature is 1000 DEG C, and the content of water, oxygen, nitrogen in inert atmosphere is 3 ppm.Material used in cladding is anti-for superhigh intensity
Nickel oxide-base superalloy powder, the powder are prepared using argon gas atomization method, and powder size is -100 ~+325 mesh, powdered
Study point (weight percent) are as follows: nickel: surplus, chromium: 9.00%, cobalt: 14.00%, carbon: 0.22%, molybdenum: 2.50%, tungsten: 4.00%,
Aluminium: 6.20%, tantalum: 6.00%, zirconium: 0.04%, boron: 0.03%, rhenium: 1.80%, hafnium: 2.00%.The technological parameter of laser melting coating are as follows: sweep
Speed: 4 mm/s is retouched, laser power: 130 ~ 230W, 1.0 mm of processing stand spot diameter, powder feeding rate: 3 g/min, single layer height
0.8 mm, overlapping rate 50%.The power of every layer of cladding successively successively decreases 20 W from the bottom up.Finally using manual grinding method to repairing
Multiple high-pressure turbine working blade blade tip external form carries out profiling polishing.Cladding layer and substrate rounding off, high-pressure turbine working leaf
Piece height meets design requirement.Using vacuum arc plating or electro beam physics vapour deposition technology again applying coating.X after reparation
Light and fluorescent penetrating inspection do not find crackle, and repairing interface has the brilliant tissue of orientation, and the high-pressure turbine working blade service life after reparation can
Reach 380 hours or more.
Claims (5)
1. a kind of restorative procedure of turbo blade blade tip crackle, which comprises the following steps:
S1. cleaning removal turbine blade surface coating；
S2. turbo blade is handled by mechanical grinding, turbo blade blade tip slit region is polished into V-groove, the opening of V-groove
Angle is 50-70 °；
S3. turbo blade blade tip is preheated by inert atmosphere high-frequency induction, preheating temperature is 900-1000 DEG C；Using imitative
Shape copper alloy hollow pipe, the logical cooling water in inside, copper coil 4 mm around blade, sensed position is Panel area；
S4. repair materials are successively accumulated along turbo blade blade tip direction of check using laser melting coating, the work of the laser melting coating
Skill parameter are as follows: scanning speed 3-4mm/s, laser power 130-230W, laser spot diameter 1mm, powder feeding rate 2-3g/
min；In the step S4, cladding material is successively accumulated along turbo blade blade tip direction of check using laser melting coating, single layer is high
Degree is 0.8mm；The laser power of every layer of cladding is successively successively decreased 20W from the bottom up；The cladding path of v-shaped openings is used in high pressure
From leaf basin to the mode of blade back cladding on the thickness direction of moving turbine blade, short path is successively accumulated, and v-shaped openings cladding is complete
It is successively accumulated further along blade tip type face afterwards to reach required blade tip height；
S5. polishing reparation, applying coating then are carried out to blade tip；
The repair materials are high-strength, antioxidant Ni-base Superalloy Powder, are made 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%, aluminium 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%, surplus are nickel；The high-strength, antioxidant nickel-base high-temperature
The partial size of alloy powder is -100 ~+325 mesh.
2. a kind of restorative procedure of turbo blade blade tip crackle according to claim 1, which is characterized in that the step S1
Another kind be selected as by mechanical grinding remove turbine blade surface coating.
3. a kind of restorative procedure of turbo blade blade tip crackle according to claim 1, which is characterized in that the step S3
In, water in inert atmosphere, oxygen, nitrogen content be respectively smaller than 10ppm.
4. a kind of restorative procedure of turbo blade blade tip crackle according to claim 1, which is characterized in that the step S5
In, polishing reparation is carried out to blade tip by manual grinding.
5. a kind of restorative procedure of turbo blade blade tip crackle according to claim 1, which is characterized in that the step S5
In, using vacuum arc plating or electro beam physics vapour deposition technology applying coating.
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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 |
| CN111850546B (en) * | 2020-06-28 | 2021-11-02 | 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 |
| 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 |
| 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 |
| 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 |
| 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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Effective date of registration: 20210823 Address after: Floor 1, building 2, No.10 Gaopeng Avenue, high tech Zone, Chengdu, Sichuan 610000 Patentee after: Chengdu Tianxiang Power Technology Research Institute Co.,Ltd. Address before: No.10 Gaopeng Avenue, high tech Zone, Chengdu, Sichuan 610000 Patentee before: PLA NO.5719 FACTORY |