JPH02258943A - High strength and high ductility al-be-li-cu-mg alloy - Google Patents
High strength and high ductility al-be-li-cu-mg alloyInfo
- Publication number
- JPH02258943A JPH02258943A JP7647989A JP7647989A JPH02258943A JP H02258943 A JPH02258943 A JP H02258943A JP 7647989 A JP7647989 A JP 7647989A JP 7647989 A JP7647989 A JP 7647989A JP H02258943 A JPH02258943 A JP H02258943A
- Authority
- JP
- Japan
- Prior art keywords
- alloy
- strength
- aircraft
- ductility
- lightweight
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 229910000861 Mg alloy Inorganic materials 0.000 title 1
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 15
- 239000000956 alloy Substances 0.000 claims abstract description 15
- 229910017818 Cu—Mg Inorganic materials 0.000 claims abstract 3
- 239000000463 material Substances 0.000 abstract description 10
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 229910000838 Al alloy Inorganic materials 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 4
- 229910000733 Li alloy Inorganic materials 0.000 description 3
- 239000001989 lithium alloy Substances 0.000 description 3
- 239000013585 weight reducing agent Substances 0.000 description 3
- 229910000714 At alloy Inorganic materials 0.000 description 2
- 230000000052 comparative effect Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 229910000979 O alloy Inorganic materials 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000007712 rapid solidification Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、例えば航空機材料に適した軽量かつ高強度特
性の優れたアルミニウム合金に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an aluminum alloy that is lightweight and has excellent high strength characteristics, suitable for example as an aircraft material.
従来、Ａｔ−Ｌｉ系合金は軽量・高強度の点から輸送用
機器、特に航空機用材料として注目されて−る。この合
金忙Ｌ１と同様低密度のＢｅを添加することにより、さ
らに軽量化が期待できる。BACKGROUND ART Conventionally, At-Li alloys have attracted attention as materials for transportation equipment, especially aircraft, because of their light weight and high strength. As with this alloy L1, further weight reduction can be expected by adding low-density Be.
また航空機用として多用されているムｔがマトリクスで
ある丸め、大きな設計変更なしに適用できることも利点
のひとつである。航空機用材料にこの合金を適用するこ
とにより、航空機の運行能率の向上および運行コストの
低減が可能となる。Another advantage is that rounding, which is often used for aircraft, is a matrix, and can be applied without major design changes. By applying this alloy to aircraft materials, it is possible to improve aircraft operating efficiency and reduce operating costs.
従来、Ａｔ−Ｌｉ系合金として、Ｏｕを添加した２０９
０合金、ＯａおよびＭｇを添加した８０９０合金等が開
発されており、一部航空機用材料として実用化されてい
た。Conventionally, 209 with O added was used as an At-Li alloy.
0 alloy, 8090 alloy to which Oa and Mg are added, etc. have been developed, and some of them have been put into practical use as materials for aircraft.
ところが、これら２０９０合金や８０９０合金は低密度
であるが（比重２．５〜２．６）、従来材料として航空
機に使用されてｈる７０００系Ａｔ合金に比べ、やや強
度、常温伸びで劣っている。航空機用材料として実用化
するためには比強度２Ｘ１０’ｍ以上、伸び１０１以上
が必要である。However, although these 2090 alloys and 8090 alloys have low density (specific gravity 2.5 to 2.6), they are slightly inferior in strength and elongation at room temperature compared to the 7000 series At alloys used in aircraft as conventional materials. There is. In order to put it into practical use as an aircraft material, it is necessary to have a specific strength of 2×10'm or more and an elongation of 101 or more.
本発明は、上記の要求を満足するような高力高延性で軽
量なムＬ合金の提供を目的としている。The object of the present invention is to provide a high-strength, high-ductility, and lightweight MU-L alloy that satisfies the above requirements.
前記目的を達成するため、本発明では、Ｂｅを添加する
ことにより材料強度を向上させるとともに、伸びも改良
することを可能としたものである。In order to achieve the above object, the present invention makes it possible to improve material strength and elongation by adding Be.
本発明だおいて、合金成分組成範囲を限定した理由を説
明する。The reason why the alloy component composition range is limited in the present invention will be explained.
Ｌｌ： ｔ Ｃｕ：０．０５ｗｔ４未満では強度が不足
し、軽量化効果が望めない。他方４． Ｃｕ：０．０５
ｗｔｅＩＩを超えると合金製造が困難で鋳塊に欠陥が多
く、製品製造においても加工性が悪−６
０ｕ： Ｑ、 ０５ ｗｔ４未満では強度が不足する。Ll: t Cu: If it is less than 0.05wt4, the strength is insufficient and no weight reduction effect can be expected. On the other hand 4. Cu:0.05
If it exceeds wteII, it is difficult to manufacture the alloy, the ingot has many defects, and the workability is poor in product manufacture.
１５０ｗｔ４を超えると加工性が低下する。If it exceeds 150wt4, workability decreases.
Ｍｇ：Ｏｕ と同様釦α０５ ｗｔｌでは強度が不足し
、１、８０ ｗｔ４を超えると加工性が低下する。Similar to Mg:Ou, the strength is insufficient for the button α05 wtl, and the workability decreases when it exceeds 1.80 wt4.
Ｚｒ： ａ Ｏ１ｖｒｔ４未満では結晶粒が微細化され
ず、伸びが低い。ｔ ００ ｗｔｌを超えると製造が困
難である。Zr: a When O1vrt4 is less, crystal grains are not refined and elongation is low. If it exceeds t 00 wtl, it is difficult to manufacture.
Ｂｅ：（ＬＱ Ｏ５ｖｔ４未満では軽量化効果、強度お
よび伸びの向上がみられない。２０ ｗｔｌを超えると
製造が困難となる。Be: (When LQ O5vt4 is less, no improvement in weight reduction effect, strength, and elongation is observed. When it exceeds 20 wtl, manufacturing becomes difficult.
ｆｓ１表に示した合金成分の各実施例および比較例の材
料につ込て、単ロール法を用いた急冷凝固により、合金
リボンを作製し、粉砕後Ａｔ缶に封して脱気、ホットプ
レス後熱間押出（押出比２１）した。１５φ押出棒を溶
体化処理後、１８０℃×２４時間時効処理し、引張試験
を行なった。An alloy ribbon was produced by rapid solidification using a single roll method by adding the materials of each example and comparative example of alloy components shown in the fs1 table, and after crushing, sealed in an At can, degassed, and hot pressed. It was then hot extruded (extrusion ratio 21). After solution treatment, a 15φ extruded rod was subjected to aging treatment at 180° C. for 24 hours, and a tensile test was conducted.
比較材としてＡｔ−Ｌｉ合金および７０７５合金も同様
にして作製し、試験を行なった。At-Li alloy and 7075 alloy were similarly prepared and tested as comparative materials.
その結果を第１表に示す。The results are shown in Table 1.
本発明は、以上説明したように構成されてｂるから、比
強度にｂＬｉａて７０００系Ａｔ合金を上回り、十分な
伸びを有する軽量ムを合金が得られた。Since the present invention is configured as described above, a lightweight alloy with specific strength exceeding the 7000 series At alloy and sufficient elongation was obtained.
Claims (1)
５〜２．５０ｗｔ％、Ｍｇ：０．０５〜１．８０ｗｔ％
、Ｚｒ：０．０１〜１．０ｗｔ％、Ｂｅ：０．００５〜
２０ｗｔ％残部Ａｌよりなる高力高延性Ａｌ−Ｂｅ−Ｌ
ｉ−Ｃｕ−Ｍｇ合金。(1) Li: 1.00-4.00wt%, Cu: 0.0
5-2.50wt%, Mg: 0.05-1.80wt%
, Zr: 0.01~1.0wt%, Be: 0.005~
High strength and high ductility Al-Be-L consisting of 20wt% balance Al
i-Cu-Mg alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7647989A JPH02258943A (en) | 1989-03-30 | 1989-03-30 | High strength and high ductility al-be-li-cu-mg alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7647989A JPH02258943A (en) | 1989-03-30 | 1989-03-30 | High strength and high ductility al-be-li-cu-mg alloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH02258943A true JPH02258943A (en) | 1990-10-19 |
Family
ID=13606331
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7647989A Pending JPH02258943A (en) | 1989-03-30 | 1989-03-30 | High strength and high ductility al-be-li-cu-mg alloy |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH02258943A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2606669C2 (en) * | 2013-09-27 | 2017-01-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Курганский государственный университет" | Method for producing alloy consisting of titanium, iron, chromium and zirconium, from aqueous suspension of particles of ores containing titanium, iron, chromium and zirconium compounds, and device therefor |
| RU2606670C2 (en) * | 2013-09-27 | 2017-01-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Курганский государственный университет" | Method for producing alloy containing titanium, iron, chromium and silicon, from aqueous suspension of particles of ores containing titanium, iron, chromium and silicon compounds, and device therefor |
| RU2634562C2 (en) * | 2015-12-11 | 2017-10-31 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Курганский государственный университет" | Method for producing "superalloy" based on titanium, aluminium, iron, chromium, copper and silicon from water suspension of particles containing compounds of these ore elements, and device for its implementation |
-
1989
- 1989-03-30 JP JP7647989A patent/JPH02258943A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2606669C2 (en) * | 2013-09-27 | 2017-01-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Курганский государственный университет" | Method for producing alloy consisting of titanium, iron, chromium and zirconium, from aqueous suspension of particles of ores containing titanium, iron, chromium and zirconium compounds, and device therefor |
| RU2606670C2 (en) * | 2013-09-27 | 2017-01-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Курганский государственный университет" | Method for producing alloy containing titanium, iron, chromium and silicon, from aqueous suspension of particles of ores containing titanium, iron, chromium and silicon compounds, and device therefor |
| RU2634562C2 (en) * | 2015-12-11 | 2017-10-31 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Курганский государственный университет" | Method for producing "superalloy" based on titanium, aluminium, iron, chromium, copper and silicon from water suspension of particles containing compounds of these ore elements, and device for its implementation |
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