JPH02258941A - High strength al-li series alloy for superplastic forming - Google Patents
High strength al-li series alloy for superplastic formingInfo
- Publication number
- JPH02258941A JPH02258941A JP1076477A JP7647789A JPH02258941A JP H02258941 A JPH02258941 A JP H02258941A JP 1076477 A JP1076477 A JP 1076477A JP 7647789 A JP7647789 A JP 7647789A JP H02258941 A JPH02258941 A JP H02258941A
- Authority
- JP
- Japan
- Prior art keywords
- alloy
- high strength
- elongation
- strength
- superplastic forming
- 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
- 239000000956 alloy Substances 0.000 title abstract description 11
- 229910045601 alloy Inorganic materials 0.000 title abstract description 11
- 239000012535 impurity Substances 0.000 claims abstract 2
- 229910000733 Li alloy Inorganic materials 0.000 claims description 3
- 239000001989 lithium alloy Substances 0.000 claims description 3
- 238000001556 precipitation Methods 0.000 abstract description 4
- 230000032683 aging Effects 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 229910000838 Al alloy Inorganic materials 0.000 abstract 3
- 229910001148 Al-Li alloy Inorganic materials 0.000 abstract 1
- 239000000463 material Substances 0.000 description 7
- 238000005266 casting Methods 0.000 description 2
- 239000013078 crystal Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 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、例えば航空機用料蹟適した軽量かつ高強度特
性の優れた超塑性成形用Ａ、１− Ｌ ｉ系合金に関す
る。DETAILED DESCRIPTION OF THE INVENTION [Industrial Field of Application] The present invention relates to an A,1-Li alloy for superplastic forming, which is lightweight and has excellent high strength characteristics, and is suitable for example for aircraft materials.
Ａｔ−Ｌｉ系合金は、軽量・高強度の点から航空機用材
料と１−て注目されている。特と近年実用化された超塑
性一体成形材は、リベット止め等の接合が不要となり、
より一層の軽量化が可能である。At-Li alloys are attracting attention as aircraft materials due to their light weight and high strength. In particular, superplastic integrally molded materials that have been put into practical use in recent years eliminate the need for joining such as riveting.
Further weight reduction is possible.
しかし、従来の材料例えば超塑性成形後の強度（時効処
理後）は、汎用の航空機付着である７０００系ＡＩ合金
に比べて低く、また伸びも低かった。However, the strength of conventional materials, such as those after superplastic forming (after aging treatment), was lower than that of 7000 series AI alloys, which are commonly used for aircraft attachment, and their elongation was also low.
本発明は、上記した点を改傍し、従来材料ｊ、：りも高
強度および伸びの高い高力Ａ１．−’Ｌｉ系合金の提供
を目的としている。The present invention improves the above-mentioned points and improves the conventional material j: high strength A1. with high strength and high elongation. -'The purpose is to provide Li-based alloys.
前記目的を達成するため、本発明は、合金成分がｒ、ｉ
：２．８０〜４００ ｗｔ４ （２，８０ｗｔ’ｌを含
まず）、Ｇｕ：［１８０〜７−５０ ｗｔ％、Ｍｇ：［
Ｌ５０−１８０ ｗｔ壬、Ｚ ｒ 二〇、０８ ＝ ＋
１２０ ｗｔｃ６、残部Ａｔならびに不可避不純物より
なる合金妬、十分な析出処理を行い、組織を均質化する
ことによって加工性及び伸びを改良し、超塑性成形後の
適切な時効処理によって、７０００系ＡＩ−合金を上回
る強度および伸びを達成することができた。In order to achieve the above object, the present invention provides that the alloy components are r, i
:2.80-400 wt4 (not including 2,80 wt'l), Gu: [180-7-50 wt%, Mg: [
L50-180 wt 壬, Z r 20, 08 = +
7000 series AI- We were able to achieve strength and elongation that exceeded that of alloys.
本発明忙おいて、各合金成分の組成範囲を限定した理由
について説明する。The reason for limiting the composition range of each alloy component in the present invention will be explained.
Ｌｉ： ２．８０ ｗｔ４以下では合金強度が不足する
。Li: Below 2.80 wt4, the alloy strength is insufficient.
また％、 ＯＯｗｔ４を超えると鋳造が困難で、鋳塊に
欠陥が多く、以後の成品製造に際しても加工性が悪くな
る。Furthermore, when the ingot exceeds 4%, casting becomes difficult, the ingot has many defects, and the workability becomes poor in subsequent production of finished products.
Ｃｕ：α８０ ｗｔ壬未満では強度が不足し、２．５０
ｗｔ４を超えると加工性が低下する。Cu: If it is less than α80 wt, the strength will be insufficient, and 2.50
If it exceeds wt4, workability decreases.
Ｍｇ：α０８ ｗｔ４未満では強度が不充分であり、ｔ
８０ ｗｔ４を超えると加工性が悪化する。Mg: α08 If it is less than wt4, the strength is insufficient, and t
If it exceeds 80 wt4, workability deteriorates.
ｚｒ：α０８ ｗｔ４未満では合金の結晶粒が微細化さ
れず、超塑性特性が劣る。α２０ ｗｔ４を超えると鋳
造が困難となる。If zr: α08 wt is less than 4, the crystal grains of the alloy will not be refined and the superplastic properties will be poor. If α20 wt4 is exceeded, casting becomes difficult.
具体例により、本発明を説明する。 The invention will be explained by specific examples.
第１表に示す合金成分の鋳塊を用い、５３０℃×２４時
間のソーキング後、４００℃×１２時間の析出処理を行
った。４００℃で２００ｔから４０ｔに鍛造した。３０
０℃×７２時間の析出処理後、面側により３０ｔとした
。４００℃で１２ｔまで圧延し、３００℃×７２時間の
析出処理を施した。３００℃で１．５ｔまで圧延し、性
能評価を行なった。Using ingots having alloy components shown in Table 1, after soaking at 530°C for 24 hours, precipitation treatment was performed at 400°C for 12 hours. It was forged from 200t to 40t at 400°C. 30
After the precipitation treatment at 0°C for 72 hours, the weight was 30t from the side. It was rolled to 12t at 400°C and subjected to precipitation treatment at 300°C for 72 hours. It was rolled to 1.5t at 300°C and its performance was evaluated.
評価方法は、圧延材を超塑性成形温度である５００℃よ
り焼入し、１６０℃×７２時間の時効処理を行い、引張
特性を調査した。In the evaluation method, the rolled material was quenched at 500°C, which is the superplastic forming temperature, and then subjected to aging treatment at 160°C for 72 hours, and the tensile properties were investigated.
調査結果を第１表に示す。The survey results are shown in Table 1.
第１表
超塑性伸びは、１．５を板縦力向において５００℃初期
歪み速度＆ ６ Ｘ １０−’／θ で引張った時の伸
びとした。For the superplastic elongation in Table 1, 1.5 was defined as the elongation when stretched at an initial strain rate of 500°C and 6 x 10-'/θ in the longitudinal force direction of the plate.
本発明合金は以上説明したように構成されているから、
第１表に示すように超塑性成形後のＴ＠ 処理により、
強度５０ ｋｇ／ｍ”以上を示すとともに、伸び１０チ
以上を示した。７４７５との比較においても比強度にお
いて優れており、航空機用超塑性材料として有望である
。Since the alloy of the present invention is constructed as explained above,
As shown in Table 1, by T@ treatment after superplastic forming,
It exhibited a strength of 50 kg/m" or more and an elongation of 10 inches or more. Compared with 7475, it was also superior in specific strength and is promising as a superplastic material for aircraft.
Claims (1)
まず）、Ｃｕ：０．８０〜２．５０ｗｔ％、Ｍｇ：０．
５０〜１．８０ｗｔ％、Ｚｒ：０．０８〜０．１５ｗｔ
％、残部Ａｌおよび不可避的不純物よりなる軽量高力Ａ
ｌ−Ｌｉ系合金。Li: 2.80 to 4.00 wt% (excluding 2.80 wt%), Cu: 0.80 to 2.50 wt%, Mg: 0.
50-1.80wt%, Zr: 0.08-0.15wt
%, the balance is Al and unavoidable impurities, lightweight and high strength A
l-Li alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1076477A JPH02258941A (en) | 1989-03-30 | 1989-03-30 | High strength al-li series alloy for superplastic forming |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1076477A JPH02258941A (en) | 1989-03-30 | 1989-03-30 | High strength al-li series alloy for superplastic forming |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH02258941A true JPH02258941A (en) | 1990-10-19 |
Family
ID=13606271
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1076477A Pending JPH02258941A (en) | 1989-03-30 | 1989-03-30 | High strength al-li series alloy for superplastic forming |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH02258941A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS605865A (en) * | 1983-03-31 | 1985-01-12 | アルカン・インタ−ナシヨナル・リミテイド | Superplastic formation for alloy material |
| JPS6156269A (en) * | 1984-07-20 | 1986-03-20 | Kobe Steel Ltd | Manufacture of super plastic al-li alloy |
| JPS61166938A (en) * | 1985-01-16 | 1986-07-28 | Kobe Steel Ltd | Al-li alloy for expansion and its production |
-
1989
- 1989-03-30 JP JP1076477A patent/JPH02258941A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS605865A (en) * | 1983-03-31 | 1985-01-12 | アルカン・インタ−ナシヨナル・リミテイド | Superplastic formation for alloy material |
| JPS6156269A (en) * | 1984-07-20 | 1986-03-20 | Kobe Steel Ltd | Manufacture of super plastic al-li alloy |
| JPS61166938A (en) * | 1985-01-16 | 1986-07-28 | Kobe Steel Ltd | Al-li alloy for expansion and its production |
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