CN103952595A - Laser-cladding powder for repairing directional solidified nickel-based high-temperature alloy blade - Google Patents
Laser-cladding powder for repairing directional solidified nickel-based high-temperature alloy blade Download PDFInfo
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- CN103952595A CN103952595A CN201410205519.3A CN201410205519A CN103952595A CN 103952595 A CN103952595 A CN 103952595A CN 201410205519 A CN201410205519 A CN 201410205519A CN 103952595 A CN103952595 A CN 103952595A
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- cladding powder
- nickel
- laser
- repairing
- temperature alloy
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- 239000000843 powder Substances 0.000 title claims abstract description 31
- 238000004372 laser cladding Methods 0.000 title claims abstract description 19
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 18
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 18
- 239000000956 alloy Substances 0.000 title claims abstract description 18
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 9
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052702 rhenium Inorganic materials 0.000 claims abstract description 6
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 6
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims abstract description 6
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 5
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 5
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052796 boron Inorganic materials 0.000 claims abstract description 5
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 5
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 5
- 239000011651 chromium Substances 0.000 claims abstract description 5
- 239000010941 cobalt Substances 0.000 claims abstract description 5
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 5
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052735 hafnium Inorganic materials 0.000 claims abstract description 5
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 5
- 239000011733 molybdenum Substances 0.000 claims abstract description 5
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 5
- 239000010937 tungsten Substances 0.000 claims abstract description 5
- 238000007711 solidification Methods 0.000 claims description 10
- 230000008023 solidification Effects 0.000 claims description 10
- 239000012535 impurity Substances 0.000 claims description 6
- 239000004411 aluminium Substances 0.000 claims description 5
- 239000000203 mixture Substances 0.000 claims description 4
- 239000000126 substance Substances 0.000 claims description 4
- -1 surplus Chemical compound 0.000 claims description 2
- 229910052729 chemical element Inorganic materials 0.000 abstract 1
- 238000005253 cladding Methods 0.000 description 9
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 238000005260 corrosion Methods 0.000 description 4
- 230000007797 corrosion Effects 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- 238000002844 melting Methods 0.000 description 4
- 208000037656 Respiratory Sounds Diseases 0.000 description 3
- 229910052786 argon Inorganic materials 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 238000002425 crystallisation Methods 0.000 description 2
- 230000008025 crystallization Effects 0.000 description 2
- 238000005530 etching Methods 0.000 description 2
- 238000009689 gas atomisation Methods 0.000 description 2
- 238000005495 investment casting Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 235000006708 antioxidants Nutrition 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 239000012254 powdered material Substances 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000003892 spreading Methods 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
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- Powder Metallurgy (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a laser-cladding powder for repairing a directional solidified nickel-based high-temperature alloy blade. The laser-cladding powder comprises the following chemical elements in percentage by weight: 15.0-16.0% of chromium, 10.0-13.0% of cobalt, 0.1-0.2% of carbon, 2.0-2.3% of molybdenum, 3.5-3.7% of tungsten, 6.5-7.0% of aluminum, 6.5-7.0% of tantalum, 0.1-0.3% of pickaxe, 0.1-0.3% of boron, 2.0-3.0% of rhenium, 1.0-1.5% of hafnium and the balance of nickel.
Description
Technical field
The present invention relates to the laser cladding powder that a kind of directional solidification nickel-base high-temperature alloy blade tip is repaired, belong to aviation and start maintenance engineering field.
Background technology
Certain type aircraft engine high-pressure turbine working blade adopts nickel-base high-temperature temperature alloy DZ125 directional freeze crystallization precision casting to form.After the time between overhaul high-pressure turbine working blade at work blade tip there is the fault such as crackle and wearing and tearing and scrap, must blade tip be repaired just and can be reused.DZ125 is high alumina, titanium superalloy, weldability is poor, adopt conventional argon arc welding easily to crack in the time of spreading blade tip, and cannot produce oriented freezing organization, therefore the main laser melting and coating technique that adopts is repaired blade tip crackle and abrading section at present both at home and abroad, but a kind of suitable cladding powder of How to choose is crucial, research and analyse and show that aircraft engine directional solidification nickel-base high-temperature alloy blade tip occurs that wearing and tearing and crack fault are mainly that reason has been aggravated wearing and tearing and crackle appearance because the higher and base material resistance to combustion gas corrosion of seal coating NiCrAlY hardness is poor etc., therefore this patent provides and has invented a kind of novel nickel-base alloy cladding powder, this powdered material has the hot strength higher than DZ125 alloy, anti-oxidant and corrosion resistance, can meet the aircraft engine requirement in work-ing life of 360 hours with the high-pressure turbine working blade of this powder reparation.
Multiple laser cladding powder is disclosed both at home and abroad, but these powder do not possess the requirement of anti-900 DEG C of above thermal etchings, and and there is thermal expansion coefficient difference > 5% between directional solidification nickel-base high temperature temperature alloy DZ125, can not meet the requirement of DZ125 directional freeze crystallization precision casting blade recovery technique.Provided by the invention good for repairing the laser cladding powder hot corrosion resistance of directional solidification nickel-base high-temperature alloy blade, and and directional solidification nickel-base high temperature temperature alloy DZ125 between there is thermal expansion coefficient difference < 5%.
Summary of the invention
The invention provides a kind ofly for repairing the laser cladding powder of directional solidification nickel-base high-temperature alloy blade, formed by following chemical composition by weight percentage: nickel, surplus, chromium 15.0～16.0%, cobalt 10.0～13.0%, carbon 0.1～0.2%, molybdenum 2.0～2.3%, tungsten 3.5～3.7%, aluminium 6.5～7.0%, tantalum 6.5～7.0%, pick 0.1～0.3%, boron 0.1～0.3%, rhenium 2.0～3.0%, hafnium 1.0～1.5%, surplus is nickel;
Abundant melting for ease of powder in laser cladding process, the bonding force of raising laser cladding layer and body material, laser cladding powder preferred size provided by the invention is-170～+ 325 object spherical powders.
For controlling the thermal expansivity of better cladding layer processed, laser cladding powder provided by the invention preferably other impurity element individual element content is not more than 0.05%, and other impurity element summations are no more than 0.1%.
In laser cladding powder provided by the invention, owing to having added the elements such as the aluminium, tantalum, rhenium of high-content, use the cladding layer corrosion resistance that this laser cladding powder obtains to be better than DZ125 alloy, this cladding layer is in the thermal etching test of 900 DEG C of insulation 100 h, its gain in weight is 4.0 mg/cm2, and the gain in weight of DZ125 alloy is 9.0 mg/cm2 under the same terms, the difference of the thermal expansivity of the thermal expansivity of this cladding layer and DZ125 alloy vane material is less than 5% simultaneously, and cladding layer interface generates mutually without fragility.
Specific embodiment
Embodiment 1, certain type aircraft engine high-pressure turbine working blade material is directional solidification nickel-base high-temperature alloy DZ125, carries out cladding reparation with the laser apparatus of 500W power, powder adopts argon gas atomization preparation, and powder morphology is spherical, the chemical composition (weight percent) of powder: nickel: surplus, chromium: 15.0%, cobalt: 12.0%, carbon: 0.15%, molybdenum: 2.1%, tungsten: 3.6%, aluminium: 6.8%, tantalum: 6.7%, pick: 0.2%, boron: 0.2%, rhenium: 2.5%, hafnium: 1.2%.Other impurity elements are Fe element, and its content is 0.04%.After laser melting coating reparation, carry out Mechanics Performance Testing, the high temperature tensile strength of 950 DEG C reaches 800 MPa, the vanes fluorescence of repairing and the demonstration of X-ray examination flawless, the high-pressure turbine working blade of reparation is through using an engine life, and blade tip occurs without falling the phenomenons such as piece.
Embodiment 2, certain type aircraft engine high-pressure turbine working blade material is directional solidification nickel-base high-temperature alloy DZ125, adopts the laser apparatus of this powder 500W power to carry out cladding reparation, powder adopts argon gas atomization preparation, and powder morphology is spherical, the chemical composition (weight percent) of powder: nickel: surplus, chromium: 15.0%, cobalt: 12.5%, carbon: 0.15%, molybdenum: 2.1%, tungsten: 3.6%, aluminium: 6.9%, tantalum: 6.7%, pick: 0.2%, boron: 0.2%, rhenium: 2.4%, hafnium: 1.3%.Other impurity elements are Fe element, and its content is 0.03%.After laser melting coating reparation, carry out Mechanics Performance Testing, the high temperature tensile strength of 950 DEG C reaches 820 MPa, the vanes fluorescence of repairing and the demonstration of X-ray examination flawless, the high-pressure turbine working blade of reparation is through using an engine life, and blade tip occurs without falling the phenomenons such as piece.
Claims (3)
1. for repairing a laser cladding powder for directional solidification nickel-base high-temperature alloy blade, it is characterized in that described laser cladding powder is made up of following chemical composition by weight percentage: nickel, surplus, chromium 15.0～16.0%, cobalt 10.0～13.0%, carbon 0.1～0.2%, molybdenum 2.0～2.3%, tungsten 3.5～3.7%, aluminium 6.5～7.0%, tantalum 6.5～7.0%, pick 0.1～0.3%, boron 0.1～0.3%, rhenium 2.0～3.0%, hafnium 1.0～1.5%, surplus is nickel.
2. laser cladding powder according to claim 1, is characterized in that, other impurity element individual element content are not more than 0.05%, and other impurity element summations are no more than 0.1%.
3. laser cladding powder according to claim 1 and 2, is characterized in that, laser cladding powder is that granularity is-170～+ 325 object spherical powders.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410205519.3A CN103952595A (en) | 2014-05-15 | 2014-05-15 | Laser-cladding powder for repairing directional solidified nickel-based high-temperature alloy blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410205519.3A CN103952595A (en) | 2014-05-15 | 2014-05-15 | Laser-cladding powder for repairing directional solidified nickel-based high-temperature alloy blade |
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|---|---|
| CN103952595A true CN103952595A (en) | 2014-07-30 |
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| CN201410205519.3A Pending CN103952595A (en) | 2014-05-15 | 2014-05-15 | Laser-cladding powder for repairing directional solidified nickel-based high-temperature alloy blade |
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| CN (1) | CN103952595A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106591826A (en) * | 2016-10-27 | 2017-04-26 | 中国人民解放军第五七九工厂 | Repair material for repairing turbine blade tip cracks and repair method thereof |
| CN109536950A (en) * | 2018-12-12 | 2019-03-29 | 江苏大学 | A kind of composite powder improving aluminum alloy heat fatigue behaviour by Laser Cladding Treatment |
| CN110303163A (en) * | 2019-05-23 | 2019-10-08 | 中国人民解放军第五七一九工厂 | A kind of high-strength high cracking resistance laser gain material reparation composite powder and preparation method |
| 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 |
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| EP1426457A2 (en) * | 2002-12-06 | 2004-06-09 | General Electric Company | Nickel-base superalloy composition and its use in single-crystal articles |
| EP1795621A1 (en) * | 2005-12-09 | 2007-06-13 | Hitachi, Ltd. | High-strength and high-ductility ni-base superalloys, parts using them, and method of producing the same |
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2014
- 2014-05-15 CN CN201410205519.3A patent/CN103952595A/en active Pending
Patent Citations (6)
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| EP1426457A2 (en) * | 2002-12-06 | 2004-06-09 | General Electric Company | Nickel-base superalloy composition and its use in single-crystal articles |
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Non-Patent Citations (1)
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106591826A (en) * | 2016-10-27 | 2017-04-26 | 中国人民解放军第五七九工厂 | Repair material for repairing turbine blade tip cracks and repair method thereof |
| CN106591826B (en) * | 2016-10-27 | 2019-11-05 | 中国人民解放军第五七一九工厂 | A kind of repair materials and its restorative procedure for repairing turbine blade tip crackle |
| CN109536950A (en) * | 2018-12-12 | 2019-03-29 | 江苏大学 | A kind of composite powder improving aluminum alloy heat fatigue behaviour by Laser Cladding Treatment |
| CN110303163A (en) * | 2019-05-23 | 2019-10-08 | 中国人民解放军第五七一九工厂 | A kind of high-strength high cracking resistance laser gain material reparation composite powder and preparation method |
| CN110303163B (en) * | 2019-05-23 | 2022-03-11 | 中国人民解放军第五七一九工厂 | High-strength and high-crack-resistance composite powder for laser additive repair and preparation method thereof |
| 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 |
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Application publication date: 20140730 |