CN104988355A - Method for reducing hot-cracking tendency of nickle-based superalloy powder material for 3D printing - Google Patents
Method for reducing hot-cracking tendency of nickle-based superalloy powder material for 3D printing Download PDFInfo
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- CN104988355A CN104988355A CN201510402000.9A CN201510402000A CN104988355A CN 104988355 A CN104988355 A CN 104988355A CN 201510402000 A CN201510402000 A CN 201510402000A CN 104988355 A CN104988355 A CN 104988355A
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Abstract
The invention discloses a method for reducing the hot-cracking tendency of a nickle-based high-temperature alloy powder material for 3D printing. Hot cracking is one of the most main defects of the high-strength nickle-based high-temperature alloy powder with high gamma minute content for 3D printing, and severely limits the application of a 3D printing process in preparation of alloy parts of this kind. The method is characterized in that by adding an element Hf or B with higher content, or adding the Hf and B in a mixing manner and then an inert gas atomization or plasma rotation electrode process is adopted to prepare supersaturated high-temperature alloy powder in a rapid-solidification manner, so that the hot-cracking sensitivity of the enhanced high-strength nickle-based alloy powder with large volume percent of gamma minute in the process of laser rapid melting and solidification. The method disclosed by the invention has the advantages that the hot-cracking defect of the high-strength nickle-based high-temperature alloy powder with high gamma minute content in the rapid temperature-rising and temperature-decreasing process of a 3D laser/electron beam rapid forming process is eliminated or reduced, and a wider process-parameter adjusting window is provided for a 3D printing part made of the high-strength nickle-based high-temperature alloy powder.
Description
Technical field
The present invention is a kind of method reducing 3D printing Ni-base Superalloy Powder material hot cracking tendency, belongs to powder metallurgy superalloy field.
Background technology
Gas turbine manufacturing technology is one of mark of the highest industrial level of country, and superalloy is called as the heart of gas turbine, is all used to manufacture gas turbine hot junction key part all the time.Improving inlet temperature before turbine is improve the most effective means of motor efficiency and thrust-weight ratio, and this also has higher requirement to the warm ability of holding of material, and in current gas turbine, hot-end component much adopts high-strength nickel base superalloy.It is a kind of technique being very suitable for engine structure complicated shape and being shaped and repairing that 3D prints, and it had both saved time and the great number cost of mold, is also subject to the restriction of part complexity sometimes unlike casting and forging process.3D prints manufacturing technology and has been applied to Titanium Alloy Aircraft structural part at present, also starts trial and is applied to manufacture engine thermal end pieces.The solution strengthening type superalloy that wherein partial intensities level is lower has 3D and prints the report of process aspect, but adopts 3D to print technique to prepare high-strength superalloy engine thermal end pieces and the case being successfully applied to gas turbine engine there is not yet report.Superalloy is because warming and cooling rate is fast in 3D print procedure, and more traditional precision casting process fusing and process of setting more easily form thermal crack.High-strength superalloy due to γ ' content higher, its hot cracking tendency also far above solution strengthening type superalloy, therefore in the past by simple technical arrangement plan be difficult to eliminate hot tearing.At present, one of maximum barrier of restriction high-strength superalloy 3D print application is exactly that its hot cracking tendency is high, and mechanical property adjustable range is narrower.
Summary of the invention
The present invention designs for above-mentioned prior art situation a kind of method reducing 3D printing Ni-base Superalloy Powder material hot cracking tendency that provides just, its objective is the element Hf by adding high level in nickel base superalloy, B or both mixtures, inert gas atomizer or plasma rotating electrode process rapid solidification is adopted to prepare supersaturation powdered alloy subsequently, reduce large volume fraction γ ' and strengthen high-strength Co-based alloy powder at 3D laser/electron beam rapid melting, hot tearing susceptibility in process of setting, for high-strength Ni-base Superalloy Powder 3D print member provides wider technical arrangement plan window.
The object of the invention is to be achieved through the following technical solutions:
The method that this kind reduces 3D printing Ni-base Superalloy Powder material hot cracking tendency is Addition ofelements Hf, B or both mixture in nickel base superalloy, wherein:
The amount of independent Addition ofelements Hf is 3.0% ~ 6.5% of nickel base superalloy quality;
The amount of independent Addition ofelements B is 0.10% ~ 0.20% of nickel base superalloy quality;
During the mixture of Addition ofelements Hf, B, the amount of element Hf is 2.0% ~ 4.0% of nickel base superalloy quality, and the amount of element B is 0.10% ~ 0.15% of nickel base superalloy quality;
Nickel base superalloy after Addition ofelements Hf, B or both mixtures prepares powdered alloy by inert gas atomizer method or plasma rotating electrode process rapid solidification.
Described powdered alloy is the supersaturation powdered alloy of uniform composition, the constituent content that this powdered alloy adds under the condition of rapid solidification can over balance solubility limit, and element segregation is limited in the small scope of fine powder inner micron pole dentrite yardstick simultaneously.This powdered alloy prints in fusing and semi-molten state in rapid melting process at laser/electron beam 3D, and in rapid solidification subsequently, be frozen into tiny dentrite tissue equally, element segregation is limited in dendrite interval micron number magnitude.Simultaneously, it is good that powder solidifies later stage fluidity of molten in the process being rapidly solidificated into block materials, fluid passage edge smoothing also keeps being communicated to lower temperature, this makes alloy solidify partial tree dendrite overlap to have higher intensity, thus prevents large volume fraction γ ' from strengthening the formation of the thermal fragmentation defect of high-strength Co-based alloy powder in 3D laser/electron beam rapid melting, process of setting.
The advantage of technical solution of the present invention is, eliminate or alleviate the thermal fragmentation defect of high γ ' content high-strength Ni-base Superalloy Powder 3D laser/electron beam fast shaping technology rapid temperature rise and drop process, for high γ ' content high-strength Ni-base Superalloy Powder 3D print member provides wider technical arrangement plan window, thus raising yield rate, yield rate improves more than 50%.
Embodiment
Embodiment 1
The inventive method is used for following nickel base superalloy, and the weight percent composition of this alloy is:
12.9Cr-20.2Co-2.0W-3.9Mo-3.5Al-3.7Ti-1.0Nb-2.3Ta-0.02C-0 .03B-0.05Zr-surplus is Ni, addition element Hf in the alloy, add-on is 3.0% of this weight alloy, prepare after the mother alloy of this alloy by vacuum induction melting remelting, supersaturation powdered alloy is prepared subsequently by argon gas atomization rapid solidification, then alloy powder sieves, size range 1 ~ 53 μm, load in vacuum or atmosphere protection hold-up vessel for subsequent use, adopt laser rapid remelting powdered alloy again and cooled and solidified becomes block materials, check that this block materials does not find thermal crack by visual and fluorescent penetrant.
Embodiment 2
The inventive method is used for following nickel base superalloy, and the weight percent composition of this alloy is:
10.4Cr-5.0Co-4.9W-4.0Mo-6.1Al-2.7Ti-0.016B-0.03C-surplus is Ni, addition element Hf in the alloy, add-on is 6.0% of this weight alloy, prepare after the mother alloy of this alloy by vacuum induction melting remelting, supersaturation powdered alloy is prepared subsequently by argon gas atomization rapid solidification, then alloy powder sieves, size range 1 ~ 53 μm, load in vacuum or atmosphere protection hold-up vessel for subsequent use, adopt laser rapid remelting powdered alloy again and cooled and solidified becomes block materials, check that this block materials does not find thermal crack by visual and fluorescent penetrant.
Embodiment 3
The inventive method is used for following nickel base superalloy, and the weight percent composition of this alloy is:
5.6Cr-12.4Co-10.1W-2.1Mo-5.4Al-1.2Ti-3.0Nb-0.056Hf-0.01C-surplus is Ni, addition element B in the alloy, add-on is 0.16% of this weight alloy, prepare after the mother alloy of this alloy by vacuum induction melting remelting, supersaturation powdered alloy is prepared subsequently by argon gas atomization rapid solidification, then alloy powder sieves, size range 1 ~ 53 μm, load in vacuum or atmosphere protection hold-up vessel for subsequent use, adopt laser rapid remelting powdered alloy again and cooled and solidified becomes block materials, check that this block materials does not find thermal crack by visual and fluorescent penetrant.
Embodiment 4
The inventive method is used for following nickel base superalloy, and the weight percent composition of this alloy is:
5.6Cr-12.4Co-10.1W-2.1Mo-5.4Al-1.2Ti-3.0Nb-0.056Hf-0.01C-surplus is Ni, addition element B in the alloy, add-on is 0.10% of this weight alloy, prepare after the mother alloy of this alloy by vacuum induction melting remelting, supersaturation powdered alloy is prepared subsequently by argon gas atomization rapid solidification, then alloy powder sieves, size range 1 ~ 53 μm, load in vacuum or atmosphere protection hold-up vessel for subsequent use, adopt laser rapid remelting powdered alloy again and cooled and solidified becomes block materials, check that this block materials does not find thermal crack by visual and fluorescent penetrant.
Embodiment 5
The inventive method is used for following nickel base superalloy, and the weight percent composition of this alloy is:
5.6Cr-12.4Co-10.1W-2.1Mo-5.4Al-1.2Ti-3.0Nb-0.056Hf-0.01C-surplus is Ni, addition element B in the alloy, add-on is 0.20% of this weight alloy, prepare after the mother alloy of this alloy by vacuum induction melting remelting, supersaturation powdered alloy is prepared subsequently by argon gas atomization rapid solidification, then alloy powder sieves, size range 1 ~ 53 μm, load in vacuum or atmosphere protection hold-up vessel for subsequent use, adopt laser rapid remelting powdered alloy again and cooled and solidified becomes block materials, check that this block materials does not find thermal crack by visual and fluorescent penetrant.
Embodiment 6
The inventive method is used for following nickel base superalloy, and the weight percent composition of this alloy is:
5.8Cr-12.4Co-10.5W-1.1Mo-5.7Al-1.2Ti-2.5Nb-0.03C-surplus is Ni, addition element Hf in the alloy, during the mixture of B, the amount of element Hf is 2.0% of nickel base superalloy quality, the amount of element B is 0.10% of nickel base superalloy quality, prepare after the mother alloy of this alloy by vacuum induction melting remelting, supersaturation powdered alloy is prepared subsequently by argon gas atomization rapid solidification, then alloy powder sieves, size range 1 ~ 53 μm, load in vacuum or atmosphere protection hold-up vessel for subsequent use, adopt laser rapid remelting powdered alloy again and cooled and solidified becomes block materials, check that this block materials does not find thermal crack by visual and fluorescent penetrant.
Embodiment 7
The inventive method is used for following nickel base superalloy, and the weight percent composition of this alloy is:
5.8Cr-12.4Co-10.5W-1.1Mo-5.7Al-1.2Ti-2.5Nb-0.03C-surplus is Ni, addition element Hf in the alloy, during the mixture of B, the amount of element Hf is 2.0% of nickel base superalloy quality, the amount of element B is 0.15% of nickel base superalloy quality, prepare after the mother alloy of this alloy by vacuum induction melting remelting, supersaturation powdered alloy is prepared subsequently by argon gas atomization rapid solidification, then alloy powder sieves, size range 1 ~ 53 μm, load in vacuum or atmosphere protection hold-up vessel for subsequent use, adopt laser rapid remelting powdered alloy again and cooled and solidified becomes block materials, check that this block materials does not find thermal crack by visual and fluorescent penetrant.
Embodiment 8
The inventive method is used for following nickel base superalloy, and the weight percent composition of this alloy is:
5.8Cr-12.4Co-10.5W-1.1Mo-5.7Al-1.2Ti-2.5Nb-0.03C-surplus is Ni, addition element Hf in the alloy, during the mixture of B, the amount of element Hf is 4.0% of nickel base superalloy quality, the amount of element B is 0.10% of nickel base superalloy quality, prepare after the mother alloy of this alloy by vacuum induction melting remelting, supersaturation powdered alloy is prepared subsequently by argon gas atomization rapid solidification, then alloy powder sieves, size range 1 ~ 53 μm, load in vacuum or atmosphere protection hold-up vessel for subsequent use, adopt laser rapid remelting powdered alloy again and cooled and solidified becomes block materials, check that this block materials does not find thermal crack by visual and fluorescent penetrant.
Claims (1)
1. reduce a method for 3D printing Ni-base Superalloy Powder material hot cracking tendency, it is characterized in that: Addition ofelements Hf, B or both mixtures in nickel base superalloy, wherein:
The amount of independent Addition ofelements Hf is 3.0% ~ 6.5% of nickel base superalloy quality;
The amount of independent Addition ofelements B is 0.10% ~ 0.20% of nickel base superalloy quality;
During the mixture of Addition ofelements Hf, B, the amount of element Hf is 2.0% ~ 4.0% of nickel base superalloy quality, and the amount of element B is 0.10% ~ 0.15% of nickel base superalloy quality;
Nickel base superalloy after Addition ofelements Hf, B or both mixtures is by preparing powdered alloy by inert gas atomizer method or plasma rotating electrode process rapid solidification.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107326218A (en) * | 2017-06-29 | 2017-11-07 | 西安欧中材料科技有限公司 | A kind of preparation method of 3D printing DD5 Ni-base Superalloy Powders |
| JP2017222929A (en) * | 2016-06-13 | 2017-12-21 | ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツングＧｅｎｅｒａｌ Ｅｌｅｃｔｒｉｃ Ｔｅｃｈｎｏｌｏｇｙ ＧｍｂＨ | Ni-BASE SUPERALLOY COMPOSITION AND METHOD FOR SLM-PROCESSING SUCH Ni-BASE SUPERALLOY COMPOSITION |
| CN111957960A (en) * | 2020-08-12 | 2020-11-20 | 南方科技大学 | Selective laser melting forming method for heat crack-free precipitation strengthening high-temperature alloy |
| CN112828289A (en) * | 2020-12-30 | 2021-05-25 | 南方科技大学 | Precipitation strengthening nickel-based high-temperature alloy laser powder bed fusion forming method capable of reducing heat cracking |
| CN115247236A (en) * | 2022-06-24 | 2022-10-28 | 华南理工大学 | NiTiHf high-temperature shape memory alloy with two-way memory effect and 4D printing method and application thereof |
-
2015
- 2015-07-09 CN CN201510402000.9A patent/CN104988355A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2017222929A (en) * | 2016-06-13 | 2017-12-21 | ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツングＧｅｎｅｒａｌ Ｅｌｅｃｔｒｉｃ Ｔｅｃｈｎｏｌｏｇｙ ＧｍｂＨ | Ni-BASE SUPERALLOY COMPOSITION AND METHOD FOR SLM-PROCESSING SUCH Ni-BASE SUPERALLOY COMPOSITION |
| JP7012459B2 (en) | 2016-06-13 | 2022-01-28 | ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツング | A Ni-based superalloy composition and a method for SLM processing such a Ni-based superalloy composition. |
| US11753705B2 (en) | 2016-06-13 | 2023-09-12 | General Electric Technology Gmbh | Ni-base superalloy composition and method for SLM processing such Ni-base superalloy composition |
| CN107326218A (en) * | 2017-06-29 | 2017-11-07 | 西安欧中材料科技有限公司 | A kind of preparation method of 3D printing DD5 Ni-base Superalloy Powders |
| CN111957960A (en) * | 2020-08-12 | 2020-11-20 | 南方科技大学 | Selective laser melting forming method for heat crack-free precipitation strengthening high-temperature alloy |
| CN112828289A (en) * | 2020-12-30 | 2021-05-25 | 南方科技大学 | Precipitation strengthening nickel-based high-temperature alloy laser powder bed fusion forming method capable of reducing heat cracking |
| CN115247236A (en) * | 2022-06-24 | 2022-10-28 | 华南理工大学 | NiTiHf high-temperature shape memory alloy with two-way memory effect and 4D printing method and application thereof |
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