CN103898502B - The method of turbine blade tip shroud Laser Cladding Carbide Hard coating - Google Patents
The method of turbine blade tip shroud Laser Cladding Carbide Hard coating Download PDFInfo
- Publication number
- CN103898502B CN103898502B CN201410143618.3A CN201410143618A CN103898502B CN 103898502 B CN103898502 B CN 103898502B CN 201410143618 A CN201410143618 A CN 201410143618A CN 103898502 B CN103898502 B CN 103898502B
- Authority
- CN
- China
- Prior art keywords
- laser
- coating
- laser melting
- melting coating
- cladding
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Laser Beam Processing (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The invention belongs to metal surface treatment technology, relate to the improvement to the coating process of turbine blade tip shroud Laser Cladding Carbide Hard.Adopt laser solid forming equipment to carry out the laser melting coating of hard alloy coating, the step of laser melting coating is as follows: blade is cleared up; Blade clamping; Cemented carbide powder vacuum drying; Laser melting coating.The present invention proposes a kind of method of turbine blade tip shroud Laser Cladding Carbide Hard coating of improvement, simplify operation, shorten the operating time, improve cladding efficiency; Meanwhile, avoid in cladding process and produce the defects such as pore, improve the quality of hard alloy coating.
Description
Technical field
The invention belongs to metal surface treatment technology, relate to the improvement to the coating process of turbine blade tip shroud Laser Cladding Carbide Hard.
Background technology
Turbine blade of gas turbine top is with integral shroud, and its effect is: utilize the friction between integral shroud to carry out absorbing vibrational energy, play damping effect.Common integral shroud shape has parallelogram and zig-zag, and zig-zag integral shroud is more conducive to the wearing and tearing suppressing vibration and reduce between integral shroud.In order to improve the wear resistance between integral shroud working face, need at integral shroud working face cladding Wimet.The coating process of current a kind of turbine blade tip shroud Laser Cladding Carbide Hard see " applied research of Turbine Sawtooth Shroud laser melting coating ", " gas turbine test and research ", the 15th volume the 2nd phase in 2012, Huang Qingnan.The step of the method is: the cemented carbide powder of cladding specific binding agent will be adopted to be bonded in need the piece surface carrying out cladding Wimet, the part of the cemented carbide powder that bondd is put into the preheating that drying baker carries out between 200 DEG C ~ 300 DEG C, then preset the surface of cemented carbide powder with laser radiation, cemented carbide powder is melted.Its shortcoming is: the first, operation is various, and the operating time is long, and cladding efficiency is low.The second, the hard alloy layer maximum ga(u)ge of cladding only has 0.3mm.Three, owing to have employed binding agent, so easily produce pore in cladding process, the quality of hard alloy coating is affected.
Summary of the invention
The object of the invention is: a kind of method proposing turbine blade tip shroud Laser Cladding Carbide Hard coating of improvement, to simplify operation, shorten the operating time, improve cladding efficiency; Meanwhile, the quality of hard alloy coating is improved.
Technical scheme of the present invention is: the method for turbine blade tip shroud Laser Cladding Carbide Hard coating, and adopt laser solid forming equipment to carry out the laser melting coating of hard alloy coating, it is characterized in that, the step of laser melting coating is as follows:
1, blade cleaning: employing absorbent cotton dips in acetone or to blade, dehydrated alcohol treats that wiping is carried out at laser melting coating position, removes the dirt treating laser melting coating position;
2, blade clamping: fixture is fixed on the Work turning table of laser solid forming equipment protection indoor, again by blades installation on fixture, blade treats the position of laser melting coating upward, relative with laser printhead, protecting sheet is pasted on the non-laser cladding surface of blade, protecting sheet is the copper sheet of thickness 0.4mm ~ 0.8mm, adopts aluminum foil and adhesive tape to be fixed by protecting sheet, closes protection room;
3, cemented carbide powder vacuum drying: CoCrMo or CoCrW cemented carbide powder is put into vacuum drying oven, be evacuated down to≤0.1Pa, be then heated to 100 DEG C ~ 120 DEG C, insulation 0.5h ~ 1h, furnace cooling is to room temperature, and the granularity of cemented carbide powder is 100 order ~ 200 orders;
4, laser melting coating: the indoor original air of applying argon gas displacement protection is carried out to atmosphere protection room; purity of argon is 99.99%; applying argon gas at least starts laser melting coating after 10min; coaxial powder-feeding nozzle is adopted synchronously to send cemented carbide powder; to turbine blade tip shroud working face cladding hard alloy coating, adopt CO
2laser apparatus, laser melting coating power 600w, sweep velocity 6mm/s, spot size 1.2mm, overlapping rate 40% ~ 50%, powder feeding rate 9 ~ 12g/min, program loop 8 ~ 10 times.
Advantage of the present invention is: a kind of method proposing turbine blade tip shroud Laser Cladding Carbide Hard coating of improvement, simplifies operation, shorten the operating time, improve cladding efficiency; Meanwhile, avoid in cladding process and produce the defects such as pore, improve the quality of hard alloy coating.
Embodiment
Below the present invention is described in further details.The method of turbine blade tip shroud Laser Cladding Carbide Hard coating, adopt laser solid forming equipment to carry out the laser melting coating of hard alloy coating, it is characterized in that, the step of laser melting coating is as follows:
1, blade cleaning: employing absorbent cotton dips in acetone or to blade, dehydrated alcohol treats that wiping is carried out at laser melting coating position, removes the dirt treating laser melting coating position;
2, blade clamping: fixture is fixed on the Work turning table of laser solid forming equipment protection indoor, again by blades installation on fixture, blade treats the position of laser melting coating upward, relative with laser printhead, protecting sheet is pasted on the non-laser cladding surface of blade, protecting sheet is the copper sheet of thickness 0.4mm ~ 0.8mm, adopts aluminum foil and adhesive tape to be fixed by protecting sheet, closes protection room;
3, cemented carbide powder vacuum drying: CoCrMo or CoCrW cemented carbide powder is put into vacuum drying oven, be evacuated down to≤0.1Pa, be then heated to 100 DEG C ~ 120 DEG C, insulation 0.5h ~ 1h, furnace cooling is to room temperature, and the granularity of cemented carbide powder is 100 order ~ 200 orders;
4, laser melting coating: the indoor original air of applying argon gas displacement protection is carried out to atmosphere protection room; purity of argon is 99.99%; applying argon gas at least starts laser melting coating after 10min; coaxial powder-feeding nozzle is adopted synchronously to send cemented carbide powder; to turbine blade tip shroud working face cladding hard alloy coating, adopt CO
2laser apparatus, laser melting coating power 600w, sweep velocity 6mm/s, spot size 1.2mm, overlapping rate 40% ~ 50%, powder feeding rate 9 ~ 12g/min, program loop 8 ~ 10 times.
Embodiment 1
1, blade cleaning: DZ125 high-temperature alloy turbine blade parallelogram integral shroud mating surface cladding Wimet, adopts absorbent cotton to dip in acetone and treats that wiping is carried out at laser melting coating position to blade, remove the dirt treating laser melting coating position
2, blade clamping: fixture is fixed on the Work turning table of laser solid forming equipment protection indoor, again by blades installation on fixture, blade treats the position of laser melting coating upward, relative with laser printhead, protecting sheet is pasted on the non-laser cladding surface of blade, protecting sheet is the copper sheet of thickness 0.4mm, adopts aluminum foil and adhesive tape to be fixed by protecting sheet, closes protection room;
3, cemented carbide powder vacuum drying: CoCrMo cemented carbide powder is put into vacuum drying oven, is evacuated down to≤0.1Pa, is then heated to 120 DEG C, insulation 1h, and furnace cooling is to room temperature, and the granularity of cemented carbide powder is 100 order ~ 200 orders;
4, laser melting coating: DZ125 high-temperature alloy turbine blade integral shroud mating surface cladding CoCrMo hard alloy layer, thickness requirement 2 ~ 3mm.The indoor original air of applying argon gas displacement protection is carried out to atmosphere protection room; purity of argon is 99.99%, starts laser melting coating after applying argon gas 12min, adopts coaxial powder-feeding nozzle synchronously to send cemented carbide powder; to turbine blade tip shroud working face cladding hard alloy coating, adopt CO
2laser apparatus, laser melting coating power 600w, sweep velocity 6mm/s, spot size 1.2mm, overlapping rate 40%, powder feeding rate 12g/min, the coating thickness determination value of single program loop is at 0.3 ± 0.04mm, and program setting circulates 9 times.
Embodiment 2
1, blade cleaning: DZ125 high-temperature alloy turbine blade zig-zag integral shroud mating surface cladding Wimet, adopts absorbent cotton to dip in acetone and treats that wiping is carried out at laser melting coating position to blade, remove the dirt treating laser melting coating position
2, blade clamping: fixture is fixed on the Work turning table of laser solid forming equipment protection indoor, again by blades installation on fixture, blade treats the position of laser melting coating upward, relative with laser printhead, protecting sheet is pasted on the non-laser cladding surface of blade, protecting sheet is the copper sheet of thickness 0.8mm, adopts aluminum foil and adhesive tape to be fixed by protecting sheet, closes protection room;
3, cemented carbide powder vacuum drying: CoCrMo cemented carbide powder is put into vacuum drying oven, is evacuated down to≤0.1Pa, is then heated to 120 DEG C, insulation 1h, and furnace cooling is to room temperature, and the granularity of cemented carbide powder is 100 order ~ 200 orders;
4, laser melting coating: DZ125 high-temperature alloy turbine blade integral shroud mating surface cladding CoCrMo hard alloy layer, thickness requirement 2 ~ 3mm.The indoor original air of applying argon gas displacement protection is carried out to atmosphere protection room; purity of argon is 99.99%, starts laser melting coating after applying argon gas 12min, adopts coaxial powder-feeding nozzle synchronously to send cemented carbide powder; to turbine blade tip shroud working face cladding hard alloy coating, adopt CO
2laser apparatus, laser melting coating power 600w, sweep velocity 6mm/s, spot size 1.2mm, overlapping rate 50%, powder feeding rate 10g/min, the coating thickness determination value of single program loop is at 0.26 ± 0.03mm, and program setting circulates 10 times.
Embodiment 3
1, blade cleaning: DZ125 high-temperature alloy turbine blade zig-zag integral shroud mating surface cladding Wimet, adopts absorbent cotton to dip in dehydrated alcohol and treats that wiping is carried out at laser melting coating position to blade, remove the dirt treating laser melting coating position
2, blade clamping: fixture is fixed on the Work turning table of laser solid forming equipment protection indoor, again by blades installation on fixture, blade treats the position of laser melting coating upward, relative with laser printhead, protecting sheet is pasted on the non-laser cladding surface of blade, protecting sheet is the copper sheet of thickness 0.8mm, adopts aluminum foil and adhesive tape to be fixed by protecting sheet, closes protection room;
3, cemented carbide powder vacuum drying: CoCrW cemented carbide powder is put into vacuum drying oven, is evacuated down to≤0.1Pa, is then heated to 120 DEG C, insulation 1h, and furnace cooling is to room temperature, and the granularity of cemented carbide powder is 100 order ~ 200 orders;
4, laser melting coating: DZ125 high-temperature alloy turbine blade integral shroud mating surface cladding CoCrW hard alloy layer, thickness requirement 2 ~ 3mm.The indoor original air of applying argon gas displacement protection is carried out to atmosphere protection room; purity of argon is 99.99%, starts laser melting coating after applying argon gas 12min, adopts coaxial powder-feeding nozzle synchronously to send cemented carbide powder; to turbine blade tip shroud working face cladding hard alloy coating, adopt CO
2laser apparatus, laser melting coating power 600w, sweep velocity 6mm/s, spot size 1.2mm, overlapping rate 50%, powder feeding rate 10g/min, the coating thickness determination value of single program loop is at 0.24 ± 0.03mm, and program setting circulates 10 times.
Claims (1)
1. the method for turbine blade tip shroud Laser Cladding Carbide Hard coating, adopt laser solid forming equipment to carry out the laser melting coating of hard alloy coating, it is characterized in that, the step of laser melting coating is as follows:
1.1, blade cleaning: employing absorbent cotton dips in acetone or to blade, dehydrated alcohol treats that wiping is carried out at laser melting coating position, removes the dirt treating laser melting coating position;
1.2, blade clamping: fixture is fixed on the Work turning table of laser solid forming equipment protection indoor, again by blades installation on fixture, blade treats the position of laser melting coating upward, relative with laser printhead, protecting sheet is pasted on the non-laser cladding surface of blade, protecting sheet is the copper sheet of thickness 0.4mm ~ 0.8mm, adopts aluminum foil and adhesive tape to be fixed by protecting sheet, closes protection room;
1.3, cemented carbide powder vacuum drying: CoCrMo or CoCrW cemented carbide powder is put into vacuum drying oven, be evacuated down to≤0.1Pa, be then heated to 100 DEG C ~ 120 DEG C, insulation 0.5h ~ 1h, furnace cooling is to room temperature, and the granularity of cemented carbide powder is 100 order ~ 200 orders;
1.4, laser melting coating: the indoor original air of applying argon gas displacement protection is carried out to atmosphere protection room; purity of argon is 99.99%; applying argon gas at least starts laser melting coating after 10min; coaxial powder-feeding nozzle is adopted synchronously to send cemented carbide powder; to turbine blade tip shroud working face cladding hard alloy coating, adopt CO
2laser apparatus, laser melting coating power 600w, sweep velocity 6mm/s, spot size 1.2mm, overlapping rate 40% ~ 50%, powder feeding rate 9 ~ 12g/min, program loop 8 ~ 10 times.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410143618.3A CN103898502B (en) | 2014-04-10 | 2014-04-10 | The method of turbine blade tip shroud Laser Cladding Carbide Hard coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410143618.3A CN103898502B (en) | 2014-04-10 | 2014-04-10 | The method of turbine blade tip shroud Laser Cladding Carbide Hard coating |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103898502A CN103898502A (en) | 2014-07-02 |
| CN103898502B true CN103898502B (en) | 2015-12-02 |
Family
ID=50990065
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410143618.3A Active CN103898502B (en) | 2014-04-10 | 2014-04-10 | The method of turbine blade tip shroud Laser Cladding Carbide Hard coating |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103898502B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106119831A (en) * | 2016-06-23 | 2016-11-16 | 中国人民解放军第五七九工厂 | The restorative procedure of Turbine Sawtooth Shroud wear-out failure |
| CN106757005B (en) * | 2016-12-29 | 2019-11-12 | 沈阳大陆激光工程技术有限公司 | A kind of laser repair method of heavy combustion engine wheel hub tenon tooth |
| CN112323063A (en) * | 2020-12-04 | 2021-02-05 | 南京铖联激光科技有限公司 | Cobalt-based high-temperature wear-resistant corrosion-resistant composite coating and preparation method thereof |
| CN114574856A (en) * | 2022-02-25 | 2022-06-03 | 苏州大学 | Ultrathin unequal-width blade laser internal powder feeding variable-spot cladding repair method and repair device |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2599384B1 (en) * | 1986-05-28 | 1988-08-05 | Alsthom | METHOD OF LAYING A COBALT-CHROME-TUNGSTEN PROTECTIVE COATING ON A TITANIUM ALLOY BLADE COMPRISING VANADIUM AND A COATED BLADE |
| CN1032147C (en) * | 1992-12-23 | 1996-06-26 | 中国华北电力联合公司北京电力设备厂 | Laser melting and coating technique for improving corrosion resistance of elements |
| CN102115882A (en) * | 2010-01-05 | 2011-07-06 | 上海工程技术大学 | Method for cladding alloy on surface of metallic matrix |
| CN102453896A (en) * | 2010-10-26 | 2012-05-16 | 沈阳大陆激光成套设备有限公司 | Method for preparing air inlet edge surface wear-resistant anti-corrosion alloy coating of tail stage blade of steam turbine |
| CN103233222A (en) * | 2013-04-17 | 2013-08-07 | 武汉点金激光科技有限公司 | Laser cladding method of steam turbine last-stage blade inlet edge surface |
| CN103276391B (en) * | 2013-06-05 | 2016-04-27 | 上海电气电站设备有限公司 | The manufacture method of a kind of final blades are water-fast erosion resisting coating |
-
2014
- 2014-04-10 CN CN201410143618.3A patent/CN103898502B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN103898502A (en) | 2014-07-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103898502B (en) | The method of turbine blade tip shroud Laser Cladding Carbide Hard coating | |
| CN106077954B (en) | Non-penetration laser welding method | |
| CN103866319A (en) | Laser cladding method for preparing nickel-based heat-resisting and wear-resisting coating on surface of zirconium alloy | |
| CN103990910B (en) | A kind of preparation method with thermal barrier coating turbine blade air film Cooling Holes | |
| CN102430849B (en) | Method for preparing single-layer diamond by means of nickel-based brazing filler metal thermal spray-welding | |
| RU2019121494A (en) | METHOD AND DEVICE FOR LOW DISTORTION WELDING WITH THE USE OF COOLING CONSISTING OF A PILLOW OF MINERAL FIBERS IMPREGNATED WITH A COOLING LIQUID | |
| CN105269158B (en) | High-energy laser step-by-step machining method for cooling hole of turbine blade with thermal barrier coating | |
| CN104960270A (en) | Interface metallurgical bonding aluminum foam slab and preparation method thereof | |
| CN104046983A (en) | Titanium alloy thin-wall blade laser-cladding low-stress local orientation cooling restoration method | |
| CN102601509A (en) | Method for welding foam aluminum sandwich composite plate | |
| CN104404302A (en) | Direct-driven rotor mechanism of wind turbine generator set | |
| CN102127729B (en) | Soldering strengthening method for thermal sprayed coating on surface of metal material | |
| CN103537881A (en) | Method for preparing alclad on surface of aluminum lithium alloy plate | |
| CN103817062B (en) | Method for coating preformed welding piece with coating | |
| CN110760841B (en) | Preparation method of amorphous nanocrystalline coating on aluminum alloy surface | |
| CN102699541A (en) | Laser cutting process for film coated metal plate | |
| CN103922613B (en) | The welding method of kovar alloy and glass | |
| CN106735904A (en) | The method for laser welding of aluminium alloy | |
| CN108598350A (en) | A kind of preparation method of the thermal cell lead with thermal Sperayed Ceramic Coatings | |
| CN104759727A (en) | Special aluminum pipe welding head | |
| WO2014199090A3 (en) | Method and unit for producing a mechanical part by sintering a powder metal material | |
| CN108971681A (en) | Shield lead welding technique to a kind of transformer copper | |
| RU2013138186A (en) | METHOD OF STELLITIC LAYING ON THE INPUT EDGE OF STEEL WORKING BLADE OF STEAM TURBINE | |
| CN109898047B (en) | Preparation method of high-reflection heat-insulation coating at end part of high-temperature vacuum heat-collecting tube | |
| CN105728876A (en) | Connection method for heat-conducting wire and metal substrate |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO,LTD. Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |