CN107964641B - Heat treatment method for improving creep forming performance of aluminum-lithium alloy - Google Patents
Heat treatment method for improving creep forming performance of aluminum-lithium alloy Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 28
- 239000001989 lithium alloy Substances 0.000 title claims abstract description 27
- 229910001148 Al-Li alloy Inorganic materials 0.000 title claims abstract description 25
- JFBZPFYRPYOZCQ-UHFFFAOYSA-N [Li].[Al] Chemical compound [Li].[Al] JFBZPFYRPYOZCQ-UHFFFAOYSA-N 0.000 title claims abstract description 25
- 238000010438 heat treatment Methods 0.000 title claims abstract description 10
- 230000032683 aging Effects 0.000 claims abstract description 25
- 238000010791 quenching Methods 0.000 claims abstract description 8
- 230000000171 quenching effect Effects 0.000 claims abstract description 8
- 238000011282 treatment Methods 0.000 claims description 16
- 238000001179 sorption measurement Methods 0.000 claims description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 7
- 230000007774 longterm Effects 0.000 claims description 6
- 229910000838 Al alloy Inorganic materials 0.000 claims description 5
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims 3
- 229910000733 Li alloy Inorganic materials 0.000 claims 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims 1
- 229910045601 alloy Inorganic materials 0.000 abstract description 20
- 239000000956 alloy Substances 0.000 abstract description 20
- 238000001556 precipitation Methods 0.000 abstract description 4
- 238000005275 alloying Methods 0.000 abstract description 2
- 239000012535 impurity Substances 0.000 abstract description 2
- 238000005728 strengthening Methods 0.000 abstract description 2
- 238000011866 long-term treatment Methods 0.000 description 6
- 239000013078 crystal Substances 0.000 description 4
- 238000004321 preservation Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000000731 high angular annular dark-field scanning transmission electron microscopy Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000003973 paint Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
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- Mechanical Engineering (AREA)
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- Organic Chemistry (AREA)
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Abstract
本发明提供了一种改善铝锂合金蠕变成形性能的热处理方法，该铝锂合金包括按重量百分比的组份：Cu1.8～2.8％，Li0.30～0.90％，Mg0.6～1.2％，微合金化元素Zr0.06～0.16％，Mn0.20～0.60％，Si≤0.05％，Fe≤0.06％，Ti≤0.15％，其它杂质单个≤0.05％，总量≤0.15％，余量为Al。其改进之处在于，将铝锂合金固溶淬火预拉伸后，在80～120℃下进行10～28h的低温长时时效后进行蠕变时效成形得到最终的析出相，欠时效态合金在蠕变过程中，强化相发生了二次析出，这使得欠时效态合金的抗蠕变性能大大优于峰时效态合金。
The invention provides a heat treatment method for improving the creep deformation performance of an aluminum-lithium alloy. The aluminum-lithium alloy comprises components by weight percentage: Cu1.8-2.8%, Li0.30-0.90%, Mg0.6-1.2% , micro-alloying elements Zr0.06～0.16%, Mn0.20～0.60%, Si≤0.05%, Fe≤0.06%, Ti≤0.15%, other impurities individually≤0.05%, the total amount≤0.15%, the balance is Al. The improvement lies in that after pre-stretching the aluminum-lithium alloy by solution quenching, it is subjected to low-temperature long-time aging at 80-120 °C for 10-28 h, and then creep-ageing is performed to obtain the final precipitation phase. During the creep process, the strengthening phase occurs secondary precipitation, which makes the creep resistance of the underaged alloy much better than that of the peak aged alloy.
Description
Technical Field
The invention relates to an aluminum lithium alloy heat treatment process, in particular to a process for improving creep forming performance of an aluminum lithium alloy.
Background
The general use of materials with high comprehensive properties such as high specific strength, high specific modulus, excellent fracture toughness and the like in the fields of aviation and aerospace and the way of integrally manufacturing the materials with large specification are combined to meet the requirements of low cost, long service life and high reliability, and the current trend is achieved. Al-Cu-Li-X aluminum-lithium alloys having high strength, toughness and damage tolerance, and having good creep deformation capability suitable for age forming are favored. The aging forming process is one of important methods for improving the comprehensive performance of the alloy, the material can deform and organize to evolve under the environment of thermal-force coupling, and the aim of improving the comprehensive performance of the alloy is achieved by regulating and controlling the precipitated phase of the alloy in the creep forming process.
Disclosure of Invention
The invention provides a method for improving the comprehensive performance of an aluminum-lithium alloy by combining the low-temperature long-time treatment after quenching and pre-stretching and the subsequent aging forming process, aiming at the requirement of integral aging forming of the aluminum-lithium alloy product, so as to promote the uniform precipitation of a precipitated phase in the alloy and adjust the crystal boundary configuration.
The technical scheme for realizing the aim of the invention is as follows:
the technical scheme of the invention is as follows: a heat treatment process for improving creep forming performance of an aluminum-lithium alloy comprises the following applicable alloy components in percentage by weight: 1.8-2.8% of main alloying element Cu0.30-0.90%, 0.6-1.2% of Mg0.06-0.16% of microalloying element Zr0.06-0.16%, 0.20-0.60% of Mn0.05% of Si, 0.06% or less of Fe, 0.15% or less of Ti, 0.05% or less of other impurities, 0.15% or less of total amount and the balance of Al.
The method is characterized in that after the aluminum lithium alloy is subjected to solution quenching and pre-stretching, low-temperature long-term aging for 10-28 hours at 80-120 ℃, a large number of atom clusters which are uniformly and dispersedly distributed are formed in a crystal, an underaging effect is generated, then creep aging forming is carried out to obtain a final precipitated phase, and a strengthening phase is subjected to secondary precipitation in the creep process of the underaged alloy, so that the creep resistance of the underaged alloy is greatly superior to that of the peak aged alloy, the crystal boundary configuration is adjusted, and the comprehensive performance of the alloy can be greatly improved. The preparation method comprises the following steps:
1.1, solution treatment: carrying out solution treatment in an air furnace or a salt bath furnace, wherein the heating temperature is 470-530 ℃, and the heat preservation time is the maximum section thickness (t) mmX (3.0-10.0) min/mm. Then carrying out water quenching on the alloy at room temperature;
1.2, pre-stretching: prestretching the quenched alloy on a prestretching machine, wherein the prestretching deformation is 2.5-7%;
1.3, low-temperature long-term treatment: carrying out low-temperature long-term treatment on the quenched alloy in a heat treatment furnace at the temperature of 80-120 ℃ for 10-28 h;
1.4, creep age forming treatment: processing the plate into parts, fixing the parts in modes of mechanical loading or vacuum adsorption and the like, and carrying out aging forming on the plate at 140-180 ℃, wherein the heat preservation time is as follows: 10 to 20 hours.
Compared with the closest prior art, the technical scheme provided by the invention has the following excellent effects:
1. the technical scheme provided by the invention has the advantages of simple process and strong industrialized feasibility;
2. the aging forming process provided by the invention has obvious comprehensive effect. The method of the invention greatly improves the comprehensive performance of the aluminum lithium alloy after creep forming.
Drawings
FIG. 1 is HAADF-STEM images of the plate microstructure after treatment according to the first embodiment and the plate microstructure without deep cooling treatment;
wherein (a) is a sample of example 1 of the present invention and (b) is an aluminum alloy sample which has not been subjected to long-term low-temperature treatment.
Detailed description of the preferred embodiments
The technical solutions provided by the present invention will be further described in detail with reference to the following specific examples, but the present invention is not limited to the following examples.
Example one
The paint comprises the following components in percentage by weight: 2.8 percent of Cu2, 0.9 percent of Li0, 0.45 percent of Mg0, 0.40 percent of Mn0, 0.12 percent of Zr0, 0.06 percent of Ti0.06 percent of Si0.05 percent of Fe0.05 percent of Al, the balance of Al, and the hot rolled aluminum-lithium alloy plate with the thickness of 80mm is subjected to solution treatment at 535 ℃ for 5 hours, and is sprayed and quenched by room temperature water. Pre-stretching the quenched plate by 4.5%, and then preserving the heat at 80 ℃ for 20h for long time aging at low temperature; and then processing the aluminum alloy plate subjected to the aging treatment into a part, fixing the obtained aluminum lithium alloy plate by using a mechanical loading or vacuum adsorption mode, and preserving the heat for 10 hours at 180 ℃ for creep aging.
The tensile strength, fracture properties, fatigue crack growth rate properties, and microstructure of the above-treated samples were measured, and the results are shown in Table 1, FIG. 1, in which (a) is a sample of example 1 of the present invention, and (b) is an aluminum alloy sample which was not subjected to low-temperature long-term treatment, as compared with an aluminum lithium alloy plate which was not subjected to low-temperature long-term treatment.
The comparison of the measured results shows that after the treatment by the method, the strength, the fracture toughness property and the fatigue crack propagation rate property of the alloy after aging forming are respectively improved, the precipitated phases in the crystal are uniformly dispersed, and the tissues after low-temperature long-term aging are more uniform and fine.
TABLE 1 comparison of Performance before and after treatment according to the method of example 1 of the present invention
Example two
The alloy comprises the following components in percentage by weight: 2.6 percent of Cu2, 0.85 percent of Li0, 0.41 percent of Mg0.38 percent of Mn0.38 percent of Zr0.12 percent of Ti0.06 percent of Si0.05 percent of Fe0.05 percent of Al, the balance of Al, and an aluminum-lithium alloy plate with the thickness of 80mm is hot-rolled for solution treatment at the temperature of 535 ℃, the heat preservation time of 5 hours, and room temperature water is sprayed for quenching. Pre-stretching the quenched plate by 4.5%, and performing long-term aging at a low temperature of 100 ℃ and keeping the temperature for 16 h; then processing the plate into a part, fixing the part in a mechanical loading or vacuum adsorption mode and the like, creep aging forming the plate at 160 ℃, and keeping the temperature for: 16 hours: the properties after age forming were measured and compared with those without low temperature long term treatment as shown in table 2.
It can be found that the strength, fracture toughness and fatigue crack propagation rate of the alloy after aging forming are improved after the alloy is treated by the method of the invention.
Table 2 comparison of performance before and after treatment according to the method of example 2 of the present invention
EXAMPLE III
The method for improving the comprehensive performance of the aluminum-lithium alloy comprises the following steps: cu2.8 percent, Li0.90 percent, Mg0.45 percent, Mn0.35 percent, Zr0.12 percent, Ti0.06 percent, Si0.05 percent, Fe0.05 percent and the balance of Al, and hot rolled plates with the thickness of 80mm are subjected to solution treatment, the temperature is 535 ℃, the heat preservation time is 5 hours, and room temperature water is sprayed and quenched. Pre-stretching the quenched plate by 5.5%, and performing long-term aging at a low temperature of 120 ℃ and keeping the temperature for 10 hours; then processing the plate into a part, fixing the part in a mechanical loading or vacuum adsorption mode and the like, creep aging forming the plate at 170 ℃, and preserving heat for a period of time: 12 hours: the properties after age forming were measured and compared with those without low temperature long term treatment as shown in table 3.
It can be found that the strength, fracture toughness and fatigue crack propagation rate of the alloy after aging forming are improved after the alloy is treated by the method of the invention.
TABLE 3 comparison of Performance before and after treatment according to the method of example 3 of the present invention
Claims (3)
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| CN109182807B (en) * | 2018-09-20 | 2020-06-30 | 北京新立机械有限责任公司 | High-strength aluminum-lithium alloy and preparation method thereof |
| CN110423966B (en) * | 2019-07-29 | 2020-09-22 | 中国航发北京航空材料研究院 | A preparation process for improving the comprehensive properties of aluminum-lithium alloy products |
| CN110512125B (en) * | 2019-08-30 | 2020-09-22 | 中国航发北京航空材料研究院 | Preparation method of diameter aluminum-lithium alloy wire for additive manufacturing |
| CN112538600A (en) * | 2020-11-10 | 2021-03-23 | 中国航发北京航空材料研究院 | Forming method of aluminum-lithium alloy complex component |
| CN112410691B (en) * | 2020-11-10 | 2021-12-24 | 中国航发北京航空材料研究院 | An Al-Li alloy material annealing process |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120048390A1 (en) * | 2010-08-25 | 2012-03-01 | Spirit Aerosystems, Inc. | Wrought and cast aluminum alloy with improved resistance to mechanical property degradation |
| CN104220616A (en) * | 2012-04-11 | 2014-12-17 | 法国肯联铝业 | Aluminum-copper-lithium alloys with improved impact resistance |
| CN106521270A (en) * | 2016-12-07 | 2017-03-22 | 中国航空工业集团公司北京航空材料研究院 | Thermal treatment process for improving corrosion resistance of aluminum-lithium alloy |
| CN106591632A (en) * | 2016-12-07 | 2017-04-26 | 中国航空工业集团公司北京航空材料研究院 | Thermal treatment process for improving comprehensive performance of aluminum-lithium alloy |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120048390A1 (en) * | 2010-08-25 | 2012-03-01 | Spirit Aerosystems, Inc. | Wrought and cast aluminum alloy with improved resistance to mechanical property degradation |
| CN104220616A (en) * | 2012-04-11 | 2014-12-17 | 法国肯联铝业 | Aluminum-copper-lithium alloys with improved impact resistance |
| CN106521270A (en) * | 2016-12-07 | 2017-03-22 | 中国航空工业集团公司北京航空材料研究院 | Thermal treatment process for improving corrosion resistance of aluminum-lithium alloy |
| CN106591632A (en) * | 2016-12-07 | 2017-04-26 | 中国航空工业集团公司北京航空材料研究院 | Thermal treatment process for improving comprehensive performance of aluminum-lithium alloy |
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