CN106119831A - The restorative procedure of Turbine Sawtooth Shroud wear-out failure - Google Patents
The restorative procedure of Turbine Sawtooth Shroud wear-out failure Download PDFInfo
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- CN106119831A CN106119831A CN201610462460.5A CN201610462460A CN106119831A CN 106119831 A CN106119831 A CN 106119831A CN 201610462460 A CN201610462460 A CN 201610462460A CN 106119831 A CN106119831 A CN 106119831A
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- Prior art keywords
- wear
- sawtooth
- turbine
- cladding
- shroud
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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
-
- 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
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C30/00—Alloys containing less than 50% by weight of each constituent
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The restorative procedure of a kind of Turbine Sawtooth Shroud wear-out failure disclosed by the invention, it is desirable to provide a kind of can be effectively improved that the anti-wear performance of Turbine Sawtooth Shroud, alloy powder matching be good, the method for near-net-shape repairing turbine blade sawtooth hat wear-out failure.The present invention is to be achieved by following technical proposals: use laser stereoforming cladding wear resistant alloy powders that sawtooth hat work surface is carried out repairing sizes, laser power is 500W, spot size is Φ 1.2 ~ Φ 1.3 mm, scanning speed is 5 ~ 6 mm/s, powder sending quantity is 11 ~ 12 g/min, accumulative cladding 3 layers；After reaching near-net-shape reparation, using 950 ± 10 DEG C, insulation 30min carries out vacuum destressing heat treatment.Sawtooth hat wearing layer shear strength after present invention reparation, hardness, fretting wear resistance property are the most superior, and it is good with matrix material matching, cold and heat fatigue strength is high, wearing layer through repeatedly cold cycling flawless, fall the faults such as block, meet the requirement of one overhaul life of electromotor.
Description
Technical field
The present invention relates to aerial motor spare part maintenance field, particularly to a kind of material be the trade mark be Ж С 6y
The restorative procedure of II grade of moving turbine blade sawtooth hat wear surface laser cladding wear alloy powder.
Background technology
II grade of moving turbine blade of aero-engine is the porous ventilation type shrouded blade become with high temperature alloy precision casting.
Afterbody is shaped with sawtooth hat structure, utilizes sawtooth hat structure to absorb vibration, extends the working life of turbo blade.Due to turbine
Blade has pneumatic Moment at work on blade, the sawtooth hat structure in long service, the fretting wear of generation, gradually
Reduce effectiveness in vibration suppression, add the risk of blade fatigue fracture.When electromotor returns factory's overhaul, more renew turbine leaf to reduce
The expense of sheet, it is necessary to the turbo blade of sawtooth hat dimension overproof is carried out resizing repairing.
The Russian side overhaul guidelines uses Arc in Hollow Cathode Vacuum Arc soldering В Ж Л 2-В И wear-resisting alloy block, the method
Step is: old wear-resistant block and the solder of integral shroud work surface dimension overproof is removed in grinding, with acetone by blade sawtooth hat with the most wear-resisting
Block cleans up, and is sandwiched in by solder thin slice between integral shroud and new wear-resisting alloy block, forms " sandwich " structure, then at vacuum chamber
In by full cathode arc to " sandwich " from side heat, after brazing filler metal melts moistening integral shroud and wear-resistant block, cooling, formed
Soldered seam.Practice finds, the method is disadvantageous in that, full cathode arc can only heat " sandwich " surface, " Sanming City
Control " fusing of the solder thin slice in centre places one's entire reliance upon conduction of heat, and controllability is poor, surface burning often occurs, and in
The heart position the most unfused phenomenon of solder thin slice, causes integral shroud surface local collapse and solder pricker unfused, non-in centre is full
Etc. defect, brazing quality is unstable, and qualification rate is low.
Prior art, in order to improve turbine blade tip shroud wearability, discloses for K403, K417 alloy vane and passes through argon
The method of arc-welding built-up welding CoCrW/CoCrMo alloy, discloses laser melting coating CoCrW alloy powder for DZ125 alloy vane
Method, above method existence is disadvantageous in that, the CoCrW/CoCrMo wearing layer of built-up welding (or cladding) and blade base material
Material thermal expansion coefficient difference is relatively big, and cold and heat fatigue strength is poor, and integral shroud CoCrW/CoCrMo wearing layer is in repeatedly cold cycling
Crackle easily occurs, falls block.
Summary of the invention
It is an object of the invention to the weak point existed for prior art the Russian side soldering, and argon arc weld deposit/laser melts
The shortcoming covering CoCrW/CoCrMo antifriction alloy, it is provided that one is simple to operate, process, qualification rate high, wearing layer performance is excellent
The restorative procedure of different Turbine Sawtooth Shroud wear-out failure.
The above-mentioned purpose of the present invention can be achieved by the following technical programs: a kind of Turbine Sawtooth Shroud abrasion event
The restorative procedure of barrier, has following technical characteristic: for II grade of turbo blade that material trademark is Ж С 6y, by repairing flow process:
Old wear-resistant block is removed in polishing and type is repaiied in solder → cleaning → laser melting coating → destressing heat treatment → polishing；Integral shroud work is removed in polishing
Make old wear-resistant block and the solder of face dimension overproof；With acetone, blade sawtooth hat work surface is cleaned up, dries；By turbo blade
Sawtooth hat work surface upward, is positioned in laser melting coating argon shield room, wear-resisting with granularity for (-100～+325) purpose Ni base
Alloy powder Ni-35-01A is cladding material, and employing laser melting coating parameter is: laser power is 500W, and spot size is Φ 1.2
~ Φ 1.3 mm, scanning speed is 5 ~ 6 mm/s, and powder sending quantity is 11 ~ 12 g/min, and sawtooth hat work surface is carried out laser melting coating
Wear-resistant alloy layer, accumulative cladding 3 layers；After reaching near-net-shape reparation, using 950 ± 10 DEG C, insulation 30min carries out vacuum and goes to answer
Power heat treatment；Repair type by mechanical grinding and recover sawtooth hat size.
The present invention has the advantages that compared to prior art.
Repairing technology process stabilization, qualification rate is high.The present invention uses the stereoforming method of cladding alloy powder to repair
Multiple Turbine Sawtooth Shroud wearing layer, it is to avoid collapse in integral shroud surface burning during Arc in Hollow Cathode Vacuum Arc soldering wear-resistant block, local
Fall into, the brazing defect such as solder pricker unfused, non-in centre is full, qualification rate is low.
Wearing layer superior performance is good with blade base matching.The present invention enters with Ni based wear-resistant alloy powder Ni-35-01A
Behavior cladding material, the coefficient of expansion phase of the wearing layer of cladding and turbo blade matrix the Ni sill of Ж С 6y (trade mark be)
Closely, the cold and heat fatigue strength of wearing layer is high, effectively overcomes CoCrW/CoCrMo wearing layer and the matrix material of built-up welding (or cladding)
Expect that repeatedly cold cycling is easily generated crackle, falls the drawback of block because thermal expansion coefficient difference is big.
Proving after tested, the sawtooth hat wearing layer bond strength using the present invention to repair is high, shear strength >=350MPa,
Far above Russia's overhaul guide specification value；Microhardness >=560 of wearing layer room temperature, carry out fretting wear in 750 DEG C of environment
Can test, the anti-wear performance of cladding layer is the most superior, and cold and heat fatigue strength is high, and structure stability is good, and integral shroud wearing layer is through many
Secondary cold cycling still flawless, fall the faults such as block, meet this h type engine h job requirement.Efficiently solve this h type engine h overhaul
In the excessive problem of II grade of turbo blade learies, not only reduce repair cost, improve economic benefit, ensure again meanwhile
Turbo blade functional reliability.
Specific embodiment mode
According to the present invention, by repairing flow process: polishing is removed at old wear-resistant block and solder → cleaning → laser melting coating → destressing heat
Type is repaiied in reason → polishing.For II grade of turbo blade of the aero-engine that material is Ж С 6y, mechanical grinding is used to remove integral shroud work
Make old wear-resistant block and the solder of face dimension overproof, with acetone, blade sawtooth hat work surface is cleaned up, dries, then by turbine
Blade sawtooth hat work surface is positioned in laser melting coating argon shield room upward, resistance to granularity for (-100～+325) purpose Ni base
Mill alloy powder Ni-35-01A is cladding material, and employing laser melting coating parameter is: laser power is 500W, and spot size is Φ
1.2～Φ 1.3 mm, scanning speed is 5～6 mm/s, and powder sending quantity is 11～12 g/min, to sawtooth hat work surface by swashing
Light stereo shaping cladding wearing layer, accumulative cladding 3 layers, after near-net-shape to be achieved is repaired, blade is put into vacuum drying oven, is warming up to
950 ± 10 DEG C, insulation 30min carries out destressing heat treatment, finally according to fitness requirement during assembling, uses mechanical grinding to repair type
Recover sawtooth hat size.
The mass fraction of Ni based wear-resistant alloy powder Ni-35-01A chemical composition: by weight percentage: Cr be (13.00～
16.00) %, Mo be (13.00～15.00) %, W be (8.50～10.00) %, Fe be (2.50～3.50) %, Al be (2.00～
3.50) %, Ti be (2.00～3.00) %, Si be (1.00～2.00) %, C be (0.12～0.18) %, B be≤0.06%, S is≤
0.02%, P are≤0.02%, and Ni is surplus.
Embodiment 1
For II grade of turbo blade 30 that the sawtooth hat abrasion size that material trademark is Ж С 6y is overproof, by repairing flow process: beat
Grind off except type is repaiied in old wear-resistant block and solder → cleaning → laser melting coating → destressing heat treatment → polishing.Idiographic flow is as follows:
(1) mechanical grinding is used to remove old wear-resistant block and the solder of integral shroud work surface dimension overproof, until exposing turbo blade saw
The matrix material of crown；
(2) it is stained with acetone wiping blade sawtooth bizet position and surrounding with cotton, goes to degrease and foul, then blade is dried；
(3) through laser cladding equipment transfer chamber transfer, blade is proceeded to argon shield room, make sawtooth hat work surface place upward
Below laser printhead, coaxial powder-feeding nozzle is used to synchronize to send (-100～+325) purpose Ni based wear-resistant alloy powder Ni-35-
01A, carries out laser cladding wear alloy-layer to blade sawtooth hat work surface and repairs size, and use optical fiber laser power is
500W, spot size is Φ 1.3mm, and scanning speed is 5mm/s, and powder sending quantity is 11g/min, use multiple tracks multilamellar cladding, road with
Road overlapping rate 45%, accumulative cladding 3 layers, reach near-net-shape reparation.
(4) turbo blade that near-net-shape is repaired being put into vacuum drying oven, be warming up to 950 DEG C, insulation 30min carries out destressing
Heat treatment.
(5) turbo blade after heat treatment uses mechanical grinding repair type and recovers sawtooth hat size, when reaching blade assembling
Fitness requirement.
Turbo blade after using above method to repair is through x-ray detection and fluorescent penetrating inspection, flawless, scarce without incomplete fusion etc.
Fall into, meet trouble shooting standard, meet the requirement of an overhaul life.
Claims (2)
1. a restorative procedure for Turbine Sawtooth Shroud wear-out failure, has a following technical characteristic: be Ж for material trademark
II grade of turbo blade of С 6y, by repairing flow process: old wear-resistant block and solder → cleaning → laser melting coating → destressing are removed in polishing
Type is repaiied in heat treatment → polishing；Old wear-resistant block and the solder of integral shroud work surface dimension overproof is removed in polishing；With acetone by blade sawtooth
Hat work surface cleans up, dries；By Turbine Sawtooth Shroud work surface upward, it is positioned in laser melting coating argon shield room,
With granularity for (-100～+325) purpose Ni based wear-resistant alloy powder Ni-35-01A as cladding material, use laser melting coating parameter
For: laser power is 500W, and spot size is Φ 1.2 ~ Φ 1.3 mm, and scanning speed is 5 ~ 6 mm/s, and powder sending quantity is 11 ~ 12
G/min, carries out laser cladding wear alloy-layer to sawtooth hat work surface, accumulative cladding 3 layers；After reaching near-net-shape reparation, adopt
With 950 ± 10 DEG C, insulation 30min carries out vacuum destressing heat treatment；Repair type by mechanical grinding and recover sawtooth hat size.
2. the restorative procedure of Turbine Sawtooth Shroud wear-out failure as claimed in claim 1, it is characterised in that: alloying studies
Point mass fraction: Cr be (13.00～16.00) %, Mo be (13.00～15.00) %, W be that (8.50～10.00) %, Fe is
(2.50～3.50) %, Al be (2.00～3.50) %, Ti be (2.00～3.00) %, Si be (1.00～2.00) %, C be (0.12
～0.18) %, B be≤0.06%, S is≤0.02%, and P is≤0.02%, and Ni is surplus.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610462460.5A CN106119831A (en) | 2016-06-23 | 2016-06-23 | The restorative procedure of Turbine Sawtooth Shroud wear-out failure |
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| CN201610462460.5A CN106119831A (en) | 2016-06-23 | 2016-06-23 | The restorative procedure of Turbine Sawtooth Shroud wear-out failure |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106862789A (en) * | 2017-03-03 | 2017-06-20 | 贵州凯阳航空发动机有限公司 | The application that K4208 alloys are welded in Low Pressure Turbine Rotor blade shroud antifriction alloy |
| CN109366009A (en) * | 2018-12-10 | 2019-02-22 | 贵州航天精工制造有限公司 | A kind of bolt assembly laser welding processing method |
| 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 |
| CN110819981A (en) * | 2019-10-21 | 2020-02-21 | 西北工业大学 | Method for repairing nickel-based single crystal turbine blade shroud |
| CN111730267A (en) * | 2020-07-03 | 2020-10-02 | 贵州乾鼎科技发展有限公司 | Welding fixture and welding method for wear-resistant block of single crystal turbine blade |
| CN111962068A (en) * | 2020-09-02 | 2020-11-20 | 湖南泰嘉新材料科技股份有限公司 | Preparation device and preparation method of band saw blade surface coating |
| CN114538961A (en) * | 2021-12-28 | 2022-05-27 | 中核四0四有限公司 | SiC/Y on surface of C-based material2O3Method for repairing coating crack |
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| CN103898502A (en) * | 2014-04-10 | 2014-07-02 | 西安航空动力股份有限公司 | Method for laser cladding of hard alloy coating on crown of turbine blade |
| CN104439617A (en) * | 2014-10-27 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Turbine blade sawtooth shroud wear-proof layer preparation method |
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Patent Citations (4)
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106862789A (en) * | 2017-03-03 | 2017-06-20 | 贵州凯阳航空发动机有限公司 | The application that K4208 alloys are welded in Low Pressure Turbine Rotor blade shroud antifriction alloy |
| CN109366009A (en) * | 2018-12-10 | 2019-02-22 | 贵州航天精工制造有限公司 | A kind of bolt assembly laser welding processing method |
| 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 |
| CN110819981A (en) * | 2019-10-21 | 2020-02-21 | 西北工业大学 | Method for repairing nickel-based single crystal turbine blade shroud |
| CN111730267A (en) * | 2020-07-03 | 2020-10-02 | 贵州乾鼎科技发展有限公司 | Welding fixture and welding method for wear-resistant block of single crystal turbine blade |
| CN111962068A (en) * | 2020-09-02 | 2020-11-20 | 湖南泰嘉新材料科技股份有限公司 | Preparation device and preparation method of band saw blade surface coating |
| CN111962068B (en) * | 2020-09-02 | 2022-09-30 | 湖南泰嘉新材料科技股份有限公司 | Preparation device and preparation method of band saw blade surface coating |
| CN114538961A (en) * | 2021-12-28 | 2022-05-27 | 中核四0四有限公司 | SiC/Y on surface of C-based material2O3Method for repairing coating crack |
| CN114538961B (en) * | 2021-12-28 | 2023-01-03 | 中核四0四有限公司 | SiC/Y on surface of C-based material 2 O 3 Method for repairing coating crack |
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