CN103540801A - High-temperature alloy - Google Patents
High-temperature alloy Download PDFInfo
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- CN103540801A CN103540801A CN201310485571.4A CN201310485571A CN103540801A CN 103540801 A CN103540801 A CN 103540801A CN 201310485571 A CN201310485571 A CN 201310485571A CN 103540801 A CN103540801 A CN 103540801A
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- superalloy
- nickel
- temperature alloy
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Abstract
The invention discloses a high-temperature alloy. The high-temperature alloy is a nickel-based high-temperature alloy. The high-temperature alloy comprises the following main elements in percentage by weight: 2-5% of chromium, 0.8-1.2% of titanium, 8-15% of aluminum and the balance of nickel and impurities, wherein the impurities comprise the following elements in percentage by weight: 0.1%-0.5% of cobalt, 0.25%-0.5% of boron, 0.04%-0.08% of tungsten, 0.08-0.1% of magnesium and 0.1%-0.5% of niobium; the total content of the main elements, namely the chromium, the titanium and the aluminum is not higher than 15%, and a main strengthening phase of the nickel-based high-temperature alloy is Ni3Al. Through the way, the high-temperature alloy disclosed by the invention has the characteristics of high strength, high temperature resistance, good plasticity and the like, can reduce porosity and improve the long-term stability of a tissue, and is suitable for casting hot end parts of aircraft engines.
Description
Technical field
The present invention relates to metal alloy compositions field, particularly relate to a kind of superalloy.
Background technology
Superalloy be a kind of can be more than 600 ℃ and the metallic substance of long term operation under certain stress condition, superalloy, according to the difference of matrix, is divided into: iron-base superalloy, nickel base superalloy and cobalt base superalloy.Wherein nickel base superalloy is optimum super heating resisting metal material, there is excellent hot strength, good anti-oxidant and hot corrosion resistance, the over-all propertieies such as good fatigue property, fracture toughness property, have become the irreplaceable critical material of turbine engine hot-end component.
But nickel base superalloy ubiquity fatigue property is slightly poor, plasticity is lower, use in structure stability decline to some extent, exist the shortcoming such as loosen, performance inconsistency is larger.
Along with the development of aviation industry, High Performance Aeroengine turbine out temperature improves day by day, and the high temperature alloy problem of engine thermal end pieces more and more highlights its importance.
Nickel base superalloy, as the main raw of manufacturing turbine blade, further improves its working temperature and improves its over-all properties, has become its development trend.
Summary of the invention
The technical problem that the present invention mainly solves is to provide a kind of superalloy, has the features such as high strength, high temperature resistant, plasticity is good, and loose minimizing, has improved and has organized permanent stability, is suitable for casting aircraft engine hot-end component.
For solving the problems of the technologies described above, the technical scheme that the present invention adopts is:
A kind of superalloy is provided, described superalloy is nickel base superalloy, its principal element and mass percent are: chromium 2-5%, titanium 0.8-1.2%, aluminium 8-15%, remaining is nickel and impurity, the contained element of described impurity and mass percent are: cobalt 0.1%-0.5%, boron 0.25%-0.5%, tungsten 0.04%-0.08%, magnesium 0.08%-0.1%, niobium 0.1%-0.5%, the total content of described principal element chromium, titanium, aluminium is not higher than 15%, and the main strengthening phase of described nickel base superalloy is Ni
3al.
In a preferred embodiment of the present invention, described main strengthening phase Ni
3al content is 40%-60%.
In a preferred embodiment of the present invention, described nickel content is not less than 85%.
The invention has the beneficial effects as follows: this alloy is nickel base superalloy, main strengthening phase is Ni
3al, adds aluminium, titanium, the chromium of rational proportion strengthening phase is strengthened, and adds the cobalt of rational proportion and can put forward heavy alloyed use temperature, adds boron, tungsten, magnesium, the niobium strengthening crystal boundary of rational proportion, improves plasticity and the intensity of alloy.
Embodiment
Below preferred embodiment of the present invention is described in detail, thereby so that advantages and features of the invention can be easier to be it will be appreciated by those skilled in the art that, protection scope of the present invention is made to more explicit defining.
The embodiment of the present invention comprises:
A kind of superalloy, described superalloy is nickel base superalloy, its principal element and mass percent are: chromium 2-5%, titanium 0.8-1.2%, aluminium 8-15%, remaining is nickel and impurity, the contained element of described impurity and mass percent are: cobalt 0.1%-0.5%, boron 0.25%-0.5%, tungsten 0.04%-0.08%, magnesium 0.08%-0.1%, niobium 0.1%-0.5%, the total content of described principal element chromium, titanium, aluminium is not higher than 15%, and the main strengthening phase of described nickel base superalloy is Ni
3al.
Wherein, described main strengthening phase Ni
3al content is 40%-60%.
And described nickel content is not less than 85%.
Embodiment mono-:
A kind of superalloy, described superalloy is nickel base superalloy, its principal element and mass percent are: chromium 2%, titanium 1%, aluminium 10%, remaining is nickel and impurity, the contained element of described impurity and mass percent are: cobalt 0.2%, boron 0.25%, tungsten 0.04%, magnesium 0.08%, niobium 0.2%, the main strengthening phase of described nickel base superalloy is Ni
3al.
Wherein, described main strengthening phase Ni
3al content is 50%.
And described nickel content is 86.23%.
Embodiment bis-:
A kind of superalloy, described superalloy is nickel base superalloy, its principal element and mass percent are: chromium 2.5%, titanium 0.9%, aluminium 10.5%, remaining is nickel and impurity, the contained element of described impurity and mass percent are: cobalt 0.3%, boron 0.25%, tungsten 0.04%, magnesium 0.08%, niobium 0.2%, the main strengthening phase of described nickel base superalloy is Ni
3al.
Wherein, described main strengthening phase Ni
3al content is 55%.
And described nickel content is 82.23 %.
This nickel base superalloy use range is 700-1200 ℃, and high anti-oxidation temperature reaches 1250 ℃, mechanical properties 800MPa, yield strength 350MPa; 1000 ℃ of tensile strengths are 150MPa, and unit elongation is 70%; 1000 ℃, creep rupture life of 30MPa stress are 250 hours, and unit elongation is 35%.
The present invention has disclosed a kind of superalloy, is nickel base superalloy, and main strengthening phase is Ni
3al, adds aluminium, titanium, the chromium of rational proportion strengthening phase is strengthened, and adds the cobalt of rational proportion and can put forward heavy alloyed use temperature, adds boron, tungsten, magnesium, the niobium strengthening crystal boundary of rational proportion, improves plasticity and the intensity of alloy.Superalloy of the present invention, has the features such as high strength, high temperature resistant, plasticity is good, and loose minimizing, has improved and has organized permanent stability, is suitable for casting aircraft engine hot-end component.
The foregoing is only embodiments of the invention; not thereby limit the scope of the claims of the present invention; every equivalent structure or conversion of equivalent flow process that utilizes description of the present invention to do; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present invention.
Claims (3)
1. a superalloy, it is characterized in that, described superalloy is nickel base superalloy, its principal element and mass percent are: chromium 2-5%, titanium 0.8-1.2%, aluminium 8-15%, remaining is nickel and impurity, the contained element of described impurity and mass percent are: cobalt 0.1%-0.5%, boron 0.25%-0.5%, tungsten 0.04%-0.08%, magnesium 0.08%-0.1%, niobium 0.1%-0.5%, and the total content of described principal element chromium, titanium, aluminium is not higher than 15%, and the main strengthening phase of described nickel base superalloy is Ni
3al.
2. superalloy according to claim 1, is characterized in that, described main strengthening phase Ni
3al content is 40%-60%.
3. superalloy according to claim 1, is characterized in that, described nickel content is not less than 85 %.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310485571.4A CN103540801A (en) | 2013-10-17 | 2013-10-17 | High-temperature alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310485571.4A CN103540801A (en) | 2013-10-17 | 2013-10-17 | High-temperature alloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103540801A true CN103540801A (en) | 2014-01-29 |
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|---|---|---|---|
| CN201310485571.4A Pending CN103540801A (en) | 2013-10-17 | 2013-10-17 | High-temperature alloy |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104926084A (en) * | 2014-03-17 | 2015-09-23 | 旭硝子株式会社 | Apparatus for manufacturing float glass and method for manufacturing float glass |
| CN108220690A (en) * | 2017-12-28 | 2018-06-29 | 沪东重机有限公司 | The forging material and forging method of a kind of exhasut valve stem peculiar to vessel |
| CN113249620A (en) * | 2021-06-25 | 2021-08-13 | 北京科技大学 | Novel delta-phase reinforced nickel-based high-temperature alloy and preparation method thereof |
| CN114790525A (en) * | 2022-04-22 | 2022-07-26 | 江苏艾速特低碳科技有限公司 | Catalyst carbon-reducing fuel economizer high-temperature alloy material and preparation method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1395125A (en) * | 1973-04-02 | 1975-05-21 | Baldwin J F | High temperature alloys |
| US4589937A (en) * | 1982-09-22 | 1986-05-20 | General Electric Company | Carbide reinforced nickel-base superalloy eutectics having improved resistance to surface carbide formation |
| JPH04358037A (en) * | 1991-03-27 | 1992-12-11 | Sumitomo Metal Ind Ltd | Nickel-base heat resisting alloy |
| JPH05239577A (en) * | 1992-02-27 | 1993-09-17 | Sumitomo Metal Ind Ltd | Nickel-base heat resistant alloy excellent in workability |
| CN103173658A (en) * | 2011-12-22 | 2013-06-26 | 株式会社日立制作所 | Nickel based forged alloy, gas turbine member using said alloy and gas turbine using said member |
-
2013
- 2013-10-17 CN CN201310485571.4A patent/CN103540801A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1395125A (en) * | 1973-04-02 | 1975-05-21 | Baldwin J F | High temperature alloys |
| US4589937A (en) * | 1982-09-22 | 1986-05-20 | General Electric Company | Carbide reinforced nickel-base superalloy eutectics having improved resistance to surface carbide formation |
| JPH04358037A (en) * | 1991-03-27 | 1992-12-11 | Sumitomo Metal Ind Ltd | Nickel-base heat resisting alloy |
| JPH05239577A (en) * | 1992-02-27 | 1993-09-17 | Sumitomo Metal Ind Ltd | Nickel-base heat resistant alloy excellent in workability |
| CN103173658A (en) * | 2011-12-22 | 2013-06-26 | 株式会社日立制作所 | Nickel based forged alloy, gas turbine member using said alloy and gas turbine using said member |
Non-Patent Citations (1)
| Title |
|---|
| 程天一等: "快速凝固Ni3Al在结构强化和研制新型高温合金中的应用", 《兵器材料科学与工程》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104926084A (en) * | 2014-03-17 | 2015-09-23 | 旭硝子株式会社 | Apparatus for manufacturing float glass and method for manufacturing float glass |
| CN108220690A (en) * | 2017-12-28 | 2018-06-29 | 沪东重机有限公司 | The forging material and forging method of a kind of exhasut valve stem peculiar to vessel |
| CN113249620A (en) * | 2021-06-25 | 2021-08-13 | 北京科技大学 | Novel delta-phase reinforced nickel-based high-temperature alloy and preparation method thereof |
| CN114790525A (en) * | 2022-04-22 | 2022-07-26 | 江苏艾速特低碳科技有限公司 | Catalyst carbon-reducing fuel economizer high-temperature alloy material and preparation method thereof |
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Application publication date: 20140129 |