CN103074525A - Nickel-based high-temperature-resistant alloy material and preparation method thereof - Google Patents
Nickel-based high-temperature-resistant alloy material and preparation method thereof Download PDFInfo
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Abstract
The invention provides a nickel-based high-temperature-resistant alloy material and a preparation method, which relates to the field of a high-temperature material. The nickel-based high-temperature-resistant alloy material comprises the following ingredients by weight percent: 0.02 to 0.03 percent of carbon (C), 18 to 19 percent of chromium (Cr), 12 to 13 percent of cobalt (Co), 4.5 to 5.1 percent of niobium (Nb), 3.2 to 3.3 percent of molybdenum (Mo), 0.4 to 0.6 percent of aluminum (Al), 0.8 to 1.2 percent of titanium (Ti), 2.5 to 3.0 percent of tantalum (Ta), 0.008 to 0.011 percent of boron (B) and balance of nickel (Ni). The preparation method comprises the following steps of preparing the materials according to the constitution of the alloy material; placing the well-prepared materials into a vacuum induction furnace to be smelted into alloy liquid; and casting the alloy liquid, and then cooling to the room temperature, so that the nickel-based high-temperature-resistant alloy material can be obtained. The nickel-based high-temperature-resistant alloy material has good cast technical property and high-temperature application property. The preparation method is simple and easy.
Description
Technical field
The present invention relates to the high-temperature material fields such as engine that Aeronautics and Astronautics, military project, heat power plant etc. use, internal combustion turbine, be specifically related to
OnePlant Ni-based high temperature alloy material and preparation method thereof.
Background technology
Superalloy is the necessary important materials of Modern Engine, rocket engine and gas turbine, has so far the history of seven more than ten years from early forties.The developing goal of superalloy will improve use temperature exactly satisfying the continuous requirement of motor efficiency and thrust, and aircraft engine increases with about 8 ℃ velocity-stabilization with the use temperature of turbine blade material every year.
Rene ' 220 alloys a kind of Ni-Cr-Co based high-temp-resistant alloy that to be the U.S. develop on Ni-Cr-Fe base alloy Inconel718 basis is compared with Inconel718, replaces Fe with Co in Rene ' 220 alloys, has increased Ta content.Owing to removed Fe in the new alloy, reduced the impact of harmful phase Laves.And with behind the Co replacement Fe, be greatly improved the creep rupture life of alloy.The increase of Ta makes alloy form a large amount of precipitation strength phases in timeliness, has remedied the loss of strength that brings owing to removing Fe.The Composition Design of Rene ' 220 alloys has increased strengthening phase γ " stability, bear high temperature capabilities and improved 50 ℃, kept simultaneously same outstanding casting technique and welding technological properties with Inconel718.The requirement that this will satisfy the High Performance Aeroengine development is the strong replacer of casting Inconel718 alloy.
But the castability of Rene ' 220 alloys and applied at elevated temperature performance are also unstable, can not satisfy the demand of Modern Engine, rocket engine and gas turbine fully.
Summary of the invention
The purpose of this invention is to provide a kind of Ni-based high temperature alloy material, have good Production Practice of Casting Technologies and applied at elevated temperature performance.
Another object of the present invention provides the preparation method of above-mentioned alloy material, and the method is simple, and the Ni-based high temperature alloy material that obtains has good Production Practice of Casting Technologies and applied at elevated temperature performance.
OnePlant Ni-based high temperature alloy material, formed by following material according to weight percentage: C 0.02-0.03%, Cr 18-19%, Co 12-13%, Nb 4.5-5.1%, Mo 3.2-3.3%, Al 0.4-0.6%, Ti 0.8-1.2%, Ta 2.5-3.0%, B 0.008-0.011%, remaining is Ni.
A kind of described Ni-based high temperature alloy material preparation method comprises the steps:
(1) prepares burden according to the composition of alloy material;
The material that (2) will prepare is put into the vacuum induction furnace smelting and is obtained aluminium alloy;
(3) aluminium alloy is cast, then be cooled to room temperature and namely get described Ni-based high temperature alloy material.
Pouring temperature is 1380-1420 ℃ in the step (3), 950-970 ℃ of mould temperature.
Beneficial effect:
The solidifying process performance of the addition alloy of boron (B) has very crucial impact in the Ni-based high temperature alloy material, and B content is lower, and the final set temperature is general also higher.When B content was 0.008-0.011% in the alloy material, the temperature range of finally solidifying of alloy material was 1100-1120 ℃.When being 0.008% such as B content, the final set temperature is 1110 temperature.When the final set temperature is 1100-1120 ℃, alloy has good feeding in final solidification stages, in the final tissue shrinkage cavity few, have good Production Practice of Casting Technologies; This final set temperature does not affect the applied at elevated temperature performance of alloy simultaneously, and alloy solid solution process also has promoter action.
The Ni-based high temperature alloy material preparation of the present invention method, simple, the Ni-based high temperature alloy material that obtains has good Production Practice of Casting Technologies and applied at elevated temperature performance.
Description of drawings
Fig. 1 is the metallographic structure figure of alloy material 1.
Fig. 2 is the metallographic structure figure of alloy material 2.
Embodiment
Embodiment 1
Composition and the weight percentage thereof of prescription 1: C 0.03%, and Cr 18.8%, and Co 12%, and Nb 5.0%, and Mo 3.2%, and Al 0.5%, and Ti 1.0%, and Ta 3.0%, and B 0.003%, and remaining is Ni.
After preparing material according to prescription 1, put into the 25Kg vacuum induction furnace, smelt and to obtain aluminium alloy.Aluminium alloy is cast, and pouring temperature is 1390 ℃, and 960 ℃ of mould temperature were cooled to room temperature in 10 minutes, obtain alloy material 1.
Alloy material 1 is put into vacuum induction furnace, be heated to 1400 ℃ of insulations after 5 minutes, cool to 1140 ℃ of insulations 10 minutes with the furnace, Fig. 1 is seen in its metallographic structure of structure observation after the shrend.As can be seen from Figure 1, mainly contain the d phase of g matrix, strip in the tissue of alloy material 1, block Laves phase and a small amount of residual liquid organized L '.
Alloy material 1 is put into vacuum induction furnace, be heated to 1400 ℃ of insulations after 5 minutes, cool to 1130 ℃ of insulations 10 minutes with the furnace, structure observation after the shrend is not found the liquid phase tissue.According to the definition of final set temperature, the final set temperature that alloy material 1 is described is 1140 ℃.
Embodiment 2
Composition and the weight percentage thereof of prescription 2: C 0.03%, and Cr 18.8%, and Co 12%, and Nb 5.0%, and Mo 3.2%, and Al 0.5%, and Ti 1.0%, and Ta 3.0%, and B 0.008%, and remaining is Ni.
Prepare material according to prescription 2, put into the 25Kg vacuum induction furnace and smelt, obtain aluminium alloy.Aluminium alloy is cast, and pouring temperature is 1390 ℃, 960 ℃ of mould temperature.In 10 minutes, be cooled to room temperature, obtain alloy material 2.
Alloy material 2 is put into vacuum induction furnace, be heated to 1400 ℃ of insulations after 5 minutes, cool to 1110 ℃ of insulations 10 minutes with the furnace, structure observation after the shrend, discovery has the liquid tissue of minute quantity, sees Fig. 2. by metallographicobservation, can find, alloy material 2 by liquid cooled to 1110 ℃ shrend after, tissue mainly contains phase among the d of g matrix, strip, block Laves phase and a small amount of residual liquid organized L '.
Alloy material 2 is put into vacuum induction furnace be heated to 1400 ℃ of insulations and cool to structure observation after 1100 ℃ of insulations shrend in 10 minutes after 5 minutes with the furnace, do not find the liquid phase tissue.According to the definition of final set temperature, the final set temperature that can determine alloy is 1110 ℃.
Embodiment 3
Composition and the weight percentage thereof of prescription 3: C 0.03%, and Cr 18.8%, and Co 12%, and Nb 4.5%, and Mo 3.2%, and Al 0.5%, and Ti 1.0%, and Ta 3.0%, and B 0.010%, and remaining is Ni.
After preparing material according to prescription 3, put into the 25Kg vacuum induction furnace and smelt and to obtain aluminium alloy.Aluminium alloy is cast, and pouring temperature is 1390 ℃, 960 ℃ of mould temperature.In 10 minutes, be cooled to room temperature, obtain alloy material 3.
Alloy material 3 is put into vacuum induction furnace, be heated to 1400 ℃ of insulations 5 minutes, cool to 1110 ℃ of insulations 10 minutes with the furnace, structure observation after the shrend, discovery has the liquid tissue of minute quantity.
Alloy material 3 is put into vacuum induction furnace be heated to 1400 ℃ of insulations 5 minutes, cool to 1100 ℃ of insulations 10 minutes with the furnace, structure observation after the shrend is not found the liquid phase tissue.The final set temperature that alloy material 3 is described is 1110 ℃.
Embodiment 4
Composition and the weight percentage thereof of prescription 4: C 0.03%, and Cr 18.8%, and Co 12%, and Nb 5.0%, and Mo 3.2%, and Al 0.5%, and Ti 1.0%, and Ta 2.5%, and B 0.011%, and remaining is Ni.
After preparing material according to prescription 4, put into the 25Kg vacuum induction furnace and smelt and to obtain aluminium alloy.Aluminium alloy is cast, and the coupon pouring temperature is 1390 ℃, 960 ℃ of mould temperature.In 10 minutes, be cooled to room temperature, obtain alloy material 4.
Alloy material 4 is put into vacuum induction furnace, is heated to 1400 ℃ of insulations 5 minutes, after cool to 1110 ℃ with the furnace, be incubated 10 minutes, structure observation after the shrend, discovery has the liquid tissue of minute quantity.
Alloy material 4 is put into vacuum induction furnace be heated to 1400 ℃ of insulations and cool to structure observation after 1100 ℃ of insulations shrend in 10 minutes after 5 minutes with the furnace, do not find the liquid phase tissue.The final set temperature that can judge alloy material 4 is 1110 ℃.
Embodiment 1-4 explanation is worked as the B addition at 0.008-0.011%, and the temperature range that alloy finally solidifies is 1100-1120 ℃, and alloy has high solidifying process performance, does not affect the applied at elevated temperature performance simultaneously.
Claims (3)
1. a Ni-based high temperature alloy material is comprised of following material according to weight percentage: C 0.02-0.03%, Cr 18-19%, Co 12-13%, Nb 4.5-5.1%, Mo 3.2-3.3%, Al 0.4-0.6%, Ti 0.8-1.2%, Ta 2.5-3.0%, B 0.008-0.011%, remaining is Ni.
2. the described Ni-based high temperature alloy material preparation method of claim 1 comprises the steps:
(1) prepares burden according to the composition of alloy material;
The material that (2) will prepare is put into the vacuum induction furnace smelting and is obtained aluminium alloy;
(3) aluminium alloy is cast, then be cooled to room temperature and namely get described Ni-based high temperature alloy material.
3. described Ni-based high temperature alloy material preparation method according to claim 2 is characterized in that pouring temperature is 1380-1420 ℃ in the step (3), 950-970 ℃ of mould temperature.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105349842A (en) * | 2015-11-06 | 2016-02-24 | 中国航空工业集团公司北京航空材料研究院 | High-temperature alloy casting resistant to high-temperature hot corrosion |
| CN106854741A (en) * | 2016-06-06 | 2017-06-16 | 中国科学院金属研究所 | A kind of heat treatment method for recovering K417G alloy properties |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101089215A (en) * | 2006-06-16 | 2007-12-19 | 中国科学院金属研究所 | High strength antithermal corrosion low segregation directional high temp alloy |
| CN101372730A (en) * | 2007-08-22 | 2009-02-25 | 中国科学院金属研究所 | Gamma''strengthened high performance casting nickel-based high-temperature alloy |
-
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- 2013-02-27 CN CN2013100609265A patent/CN103074525A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101089215A (en) * | 2006-06-16 | 2007-12-19 | 中国科学院金属研究所 | High strength antithermal corrosion low segregation directional high temp alloy |
| CN101372730A (en) * | 2007-08-22 | 2009-02-25 | 中国科学院金属研究所 | Gamma''strengthened high performance casting nickel-based high-temperature alloy |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105349842A (en) * | 2015-11-06 | 2016-02-24 | 中国航空工业集团公司北京航空材料研究院 | High-temperature alloy casting resistant to high-temperature hot corrosion |
| CN105349842B (en) * | 2015-11-06 | 2017-06-13 | 中国航空工业集团公司北京航空材料研究院 | A kind of high temperature heat-resistant corrodes high-temperature alloy casting |
| CN106854741A (en) * | 2016-06-06 | 2017-06-16 | 中国科学院金属研究所 | A kind of heat treatment method for recovering K417G alloy properties |
| CN106854741B (en) * | 2016-06-06 | 2018-07-10 | 中国科学院金属研究所 | A kind of heat treatment method for restoring K417G alloy properties |
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Application publication date: 20130501 |