CN104018045A - Aviation casting heat-resistant aluminum alloy and thermal treatment method thereof - Google Patents
Aviation casting heat-resistant aluminum alloy and thermal treatment method thereof Download PDFInfo
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- CN104018045A CN104018045A CN201410276275.8A CN201410276275A CN104018045A CN 104018045 A CN104018045 A CN 104018045A CN 201410276275 A CN201410276275 A CN 201410276275A CN 104018045 A CN104018045 A CN 104018045A
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Abstract
The invention discloses aviation casting heat-resistant aluminum alloy and a thermal treatment method thereof. The aviation casting heat-resistant aluminum alloy comprises the following chemical components in percentage by weight: 1.3-1.5 of Mg, 4-5 of Cu, 0.6-0.8 of Mn, 0.1-0.2 of Ag, 0.5-0.6 of Si, 0.6-0.8 of Fe, 0.1-0.2 of Nd, 0.1-0.2 of Pm, 0.15-0.2 of Eu, 0.15-0.2 of Sm, 0.1-0.3 of Zn, 0.1-0.2 of Cr, 0.1-0.15 of Cd and the balance of Al and unavoidable impurities. The aviation casting heat-resistant aluminum alloy is high in strength, resistant to high temperature and wear, greatly improved in comprehensive performance and capable of meeting the requirement of an aviation technology.
Description
Technical field
The invention belongs to aeronautical material technical field, relate in particular to a kind of Aeronautical Cast and make heat-resisting aluminium alloy and heat treating method thereof.
Background technology
Cast aluminium alloy is used in a large number in aeronautical technology field, and the developing direction of cast aluminium alloy is exactly high strength, high temperature resistant, and wear-resisting, improves material purity, complex alloys.
Summary of the invention
Technical problem to be solved by this invention is to provide a kind of high strength, and high temperature resistant and wear-resisting Aeronautical Cast is made heat-resisting aluminium alloy and heat treating method thereof.
In order to solve the problems of the technologies described above, the technical solution adopted in the present invention is: a kind of Aeronautical Cast is made heat-resisting aluminium alloy, and its chemical component weight per-cent is: Mg1.3-1.5, Cu4-5, Mn0.6-0.8, Ag0.1-0.2, Si0.5-0.6, Fe0.6-0.8, Nd0.1-0.2, Pm0.1-0.2, Eu0.15-0.2, Sm0.15-0.2, Zn0.1-0.3, Cr0.1-0.2, Cd0.1-0.15, all the other are Al and inevitable impurity.
Its chemical component weight per-cent is: Mg1.4-1.5, Cu4-4.4, Mn0.6-0.7, Ag0.1-0.13, Si0.5-0.6, Fe0.7-0.8, Nd0.15-0.2, Pm0.18-0.2, Eu0.15-0.0.17, Sm0.15-0.16, Zn0.1-0.3, Cr0.1-0.2, Cd0.12-0.15, all the other are Al and inevitable impurity.
A kind of above-mentioned Aeronautical Cast is made the heat treating method of heat-resisting aluminium alloy, the parts of alloy casting adopt 500 °～550 ° to keep 13～15h solution treatment to quench, 180 °～200 ° keep 7～9h ageing treatment, and adopt hot isostatic pressing technique: 1200 °～1500 °, 100～110MPa are processed 2h.
The parts of alloy casting adopt 530 ° to keep 14h solution treatment to quench, and 190 ° keep 8h ageing treatment, and adopt hot isostatic pressing technique: 1200 °～1500 °, 100～110MPa are processed 2h.
Add Cu can put forward heavy alloyed intensity and thermotolerance, Al-Cu alloy adds transition element can further improve thermotolerance, add rare earth element can further improve its thermotolerance at this class alloy, select neodymium (Nd), promethium (Pm), europium (Eu), samarium (Sm), the synergy of these rare earth element combinations improves thermotolerance and the wear resistance of cast aluminium alloy greatly.
Add Ag can improve precipitation strength effect, improve alloy strength.
Add Si can form Al-Si eutectic and there is good mobility, castability excellence, rotten processing can thinning microstructure.
Add Mg can there is good corrosion stability and machinability.
Add Zn not heat-treat.
Add Cr can improve wear resisting property.For the main structure of aircraft.
Adopt high-quality casting technology, adopt hot isostatic pressing technique, improve the performance of cast aluminium alloy.
A technical scheme tool in technique scheme has the following advantages or beneficial effect, and above-mentioned cast aluminium alloy has high strength, high temperature resistant, and wear resisting property improves over-all properties greatly, meets aeronautical technology needs.
Embodiment
For making the object, technical solutions and advantages of the present invention clearer, below embodiment of the present invention is described further in detail.
Embodiment mono-
Add Cu can put forward heavy alloyed intensity and thermotolerance, Al-Cu alloy adds transition element can further improve thermotolerance, select neodymium (Nd), promethium (Pm), europium (Eu), samarium (Sm), the synergy of these rare earth element combinations improves thermotolerance and the wear resistance of cast aluminium alloy greatly.
Add Ag can improve precipitation strength effect, improve alloy strength.Add Si can form Al-Si eutectic and there is good mobility, castability excellence, rotten processing can thinning microstructure.Add Mg can there is good corrosion stability and machinability.Add Zn not heat-treat.Add Cr can improve wear resisting property.For the main structure of aircraft.
Above-mentioned cast aluminium alloy has high strength, high temperature resistant, and wear resisting property improves over-all properties greatly, meets aeronautical technology needs.
Embodiment bis-
Add Cu can put forward heavy alloyed intensity and thermotolerance, Al-Cu alloy adds transition element can further improve thermotolerance, select neodymium (Nd), promethium (Pm), europium (Eu), samarium (Sm), the synergy of these rare earth element combinations improves thermotolerance and the wear resistance of cast aluminium alloy greatly.
Add Ag can improve precipitation strength effect, improve alloy strength.Add Si can form Al-Si eutectic and there is good mobility, castability excellence, rotten processing can thinning microstructure.Add Mg can there is good corrosion stability and machinability.Add Zn not heat-treat.Add Cr can improve wear resisting property.For the main structure of aircraft.
Above-mentioned cast aluminium alloy has high strength, high temperature resistant, and wear resisting property improves over-all properties greatly, meets aeronautical technology needs.
Embodiment tri-
Add Cu can put forward heavy alloyed intensity and thermotolerance, Al-Cu alloy adds transition element can further improve thermotolerance, select neodymium (Nd), promethium (Pm), europium (Eu), samarium (Sm), the synergy of these rare earth element combinations improves thermotolerance and the wear resistance of cast aluminium alloy greatly.
Add Ag can improve precipitation strength effect, improve alloy strength.Add Si can form Al-Si eutectic and there is good mobility, castability excellence, rotten processing can thinning microstructure.Add Mg can there is good corrosion stability and machinability.Add Zn not heat-treat.
Above-mentioned cast aluminium alloy has high strength, high temperature resistant, and wear resisting property improves over-all properties greatly, meets aeronautical technology needs.
Embodiment tetra-
Above-mentioned Aeronautical Cast is made a heat treating method for heat-resisting aluminium alloy, and the parts of alloy casting adopt 53 ° to keep 14h solution treatment to quench, and 190 ° keep 8h ageing treatment, and adopt hot isostatic pressing technique: 1300 °, 100MPa are processed 2h.On the basis of improving in density, can obtain tiny uniform grain structure, intensity and toughness are all improved.
Above the present invention is exemplarily described; obviously specific implementation of the present invention is not subject to the restrictions described above; as long as adopted the improvement of the various unsubstantialities that method of the present invention design and technical scheme carry out; or without improving, design of the present invention and technical scheme are directly applied to other occasion, all within protection scope of the present invention.
Claims (4)
1. Aeronautical Cast is made a heat-resisting aluminium alloy, it is characterized in that, its chemical component weight per-cent is: Mg1.3-1.5, Cu4-5, Mn0.6-0.8, Ag0.1-0.2, Si0.5-0.6, Fe0.6-0.8, Nd0.1-0.2, Pm0.1-0.2, Eu0.15-0.2, Sm0.15-0.2, Zn0.1-0.3, Cr0.1-0.2, Cd0.1-0.15, all the other are Al and inevitable impurity.
2. Aeronautical Cast as claimed in claim 1 is made heat-resisting aluminium alloy, it is characterized in that, its chemical component weight per-cent is: Mg1.4-1.5, Cu4-4.4, Mn0.6-0.7, Ag0.1-0.13, Si0.5-0.6, Fe0.7-0.8, Nd0.15-0.2, Pm0.18-0.2, Eu0.15-0.0.17, Sm0.15-0.16, Zn0.1-0.3, Cr0.1-0.2, Cd0.12-0.15, all the other are Al and inevitable impurity.
3. an Aeronautical Cast as claimed in claim 1 or 2 is made the heat treating method of heat-resisting aluminium alloy, it is characterized in that, the parts of alloy casting adopt 500 °～550 ° to keep 13～15h solution treatment to quench, 180 °～200 ° keep 7～9h ageing treatment, and adopt hot isostatic pressing technique: 1200 °～1500 °, 100～110MPa are processed 2h.
4. Aeronautical Cast as claimed in claim 3 is made the heat treating method of heat-resisting aluminium alloy, it is characterized in that, the parts of alloy casting adopt 530 ° to keep 14h solution treatment to quench, 190 ° keep 8h ageing treatment, and adopt hot isostatic pressing technique: 1200 °～1500 °, 100～110MPa are processed 2h.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201410276275.8A CN104018045A (en) | 2014-06-19 | 2014-06-19 | Aviation casting heat-resistant aluminum alloy and thermal treatment method thereof |
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| CN201410276275.8A CN104018045A (en) | 2014-06-19 | 2014-06-19 | Aviation casting heat-resistant aluminum alloy and thermal treatment method thereof |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5066342A (en) * | 1988-01-28 | 1991-11-19 | Aluminum Company Of America | Aluminum-lithium alloys and method of making the same |
| WO2002020862A2 (en) * | 2000-09-04 | 2002-03-14 | Impol, Industrija Metalnih Polizdelkov, D.D. | Aluminum free cutting alloys, recycling process for the manufacture thereof and their use |
| CN101805848A (en) * | 2009-09-17 | 2010-08-18 | 贵州华科铝材料工程技术研究有限公司 | Be-Co-RE high-strength heat resistant aluminum alloy material modified with C and preparation method thereof |
-
2014
- 2014-06-19 CN CN201410276275.8A patent/CN104018045A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5066342A (en) * | 1988-01-28 | 1991-11-19 | Aluminum Company Of America | Aluminum-lithium alloys and method of making the same |
| WO2002020862A2 (en) * | 2000-09-04 | 2002-03-14 | Impol, Industrija Metalnih Polizdelkov, D.D. | Aluminum free cutting alloys, recycling process for the manufacture thereof and their use |
| CN101805848A (en) * | 2009-09-17 | 2010-08-18 | 贵州华科铝材料工程技术研究有限公司 | Be-Co-RE high-strength heat resistant aluminum alloy material modified with C and preparation method thereof |
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Application publication date: 20140903 |
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