JPH0310040A - High ductility al-li-zr alloy - Google Patents
High ductility al-li-zr alloyInfo
- Publication number
- JPH0310040A JPH0310040A JP14301089A JP14301089A JPH0310040A JP H0310040 A JPH0310040 A JP H0310040A JP 14301089 A JP14301089 A JP 14301089A JP 14301089 A JP14301089 A JP 14301089A JP H0310040 A JPH0310040 A JP H0310040A
- Authority
- JP
- Japan
- Prior art keywords
- alloy
- break
- elongation
- low
- strength
- 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
- 229910001093 Zr alloy Inorganic materials 0.000 title abstract description 4
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 14
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 13
- 229910052698 phosphorus Inorganic materials 0.000 claims abstract description 10
- 229910001148 Al-Li alloy Inorganic materials 0.000 claims abstract description 9
- 229910052717 sulfur Inorganic materials 0.000 claims abstract description 8
- 239000012535 impurity Substances 0.000 claims abstract description 3
- 239000000956 alloy Substances 0.000 abstract description 16
- 239000000463 material Substances 0.000 abstract description 13
- 229910045601 alloy Inorganic materials 0.000 abstract description 11
- 230000002542 deteriorative effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 5
- 239000000843 powder Substances 0.000 description 5
- 229910052782 aluminium Inorganic materials 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 239000001989 lithium alloy Substances 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000001953 recrystallisation Methods 0.000 description 2
- 238000009864 tensile test Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910000733 Li alloy Inorganic materials 0.000 description 1
- -1 Li-X -Li (X=B Inorganic materials 0.000 description 1
- 229910006270 Li—Li Inorganic materials 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000005097 cold rolling Methods 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000002860 competitive effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000009689 gas atomisation Methods 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000005098 hot rolling Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L24/00—Arrangements for connecting or disconnecting semiconductor or solid-state bodies; Methods or apparatus related thereto
- H01L24/74—Apparatus for manufacturing arrangements for connecting or disconnecting semiconductor or solid-state bodies
- H01L24/79—Apparatus for Tape Automated Bonding [TAB]
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Computer Hardware Design (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Power Engineering (AREA)
- Powder Metallurgy (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、航空機材料として注目されている軽量かつ高
弾性率を持つＡｌ−Ｌｉ基合金に関するものである。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an Al-Li based alloy that is lightweight and has a high modulus of elasticity and is attracting attention as an aircraft material.
航空機用材料は、比重の小さなＡ１合金が使用され、例
えば、ＡＡ２０２４やＡＡ７０５０で示されるＡ１合金
材料が使用されている。しかし、これらのＡ１合金材料
は、強度の増加に伴って靭性が低下する性質がある。ま
た、アルミニウム合金において比重を減少させるために
Ｌｉを添加することがおこなわれているが、Ｌｉを添加
すると、ますます靭性が低下する結果となって、航空機
用材料としてＡｌ−Ｌｉ合金は、実用化されていないの
が実情である。As the aircraft material, an A1 alloy having a small specific gravity is used, for example, an A1 alloy material designated as AA2024 or AA7050 is used. However, these A1 alloy materials have the property that their toughness decreases as their strength increases. Additionally, Li is added to aluminum alloys to reduce their specific gravity, but the addition of Li further reduces the toughness, making Al-Li alloys impractical as aircraft materials. The reality is that it has not been standardized.
従来使用されてきた２０９０合金および８０９０合金は
、低密度であるが（２，５〜２．６ｇ／ａＩ）従来航空
機に使用されている７０００系合金に比較して、強度・
伸びにおいて劣っている。The conventionally used 2090 and 8090 alloys have low density (2.5 to 2.6 g/aI), but have higher strength and strength than the 7000 series alloys conventionally used in aircraft.
It is inferior in elongation.
航空機用材料として実用化するためには、比強度２Ｘ１
０ ｍｍ以上、伸び１０％以上が必要である。In order to put it to practical use as an aircraft material, a specific strength of 2X1 is required.
0 mm or more and elongation of 10% or more are required.
しかし、このようなＡｌ−Ｌｉ基合金は、粒界破壊が生
じやすいために強度および延性が低下するという欠点を
有する。この粒界破壊は粒界にＮａおよびＬｉが偏析し
やすいために生じるものである。したがって、Ａｌ−Ｌ
ｉ基合金は、従来の航空機材料である７０００系Ａ１合
金に比べて問題があり、上述のようにまだ実用化されて
いないのが実情である。However, such Al-Li-based alloys have the disadvantage that intergranular fracture tends to occur, resulting in reduced strength and ductility. This grain boundary fracture occurs because Na and Li tend to segregate at grain boundaries. Therefore, Al-L
The i-base alloy has problems compared to the 7000 series A1 alloy, which is a conventional aircraft material, and the fact is that it has not yet been put into practical use as described above.
本発明は、上記の問題点を解消し、引張強度は従来のＡ
ｌ−Ｌｉ合金と変わりなく、破断伸びが１２％以上を有
するＡｌ−Ｌｉアルミニウム合金を提供することを目的
としている。The present invention solves the above problems, and the tensile strength is lower than that of the conventional A.
The object of the present invention is to provide an Al-Li aluminum alloy having an elongation at break of 12% or more, which is the same as the l-Li alloy.
本発明者は、上記目的を達成するために種々研究を重ね
た結果、本発明は、Ｌｉ：１．ＱＱ〜４．００％、Ｚｒ
：０．０１〜０．２０％およびＢ：０．００２〜１．０
％、Ｃ：０．０１〜１゜０％、Ｎ：０．０１〜１．０％
、Ｐ：０．００１〜１１．０％、Ｓ：０．００１〜１．
０％のうちの一種または二種以上を含有し、残部Ａｌお
よび不可避的不純物からなる高延性Ａｌ−Ｌｉ−Ｚｒ合
金を要旨とするものである。The present inventor has conducted various studies in order to achieve the above object, and as a result, the present invention has been developed based on Li:1. QQ~4.00%, Zr
:0.01~0.20% and B:0.002~1.0
%, C: 0.01-1°0%, N: 0.01-1.0%
, P: 0.001-11.0%, S: 0.001-1.
The gist is a highly ductile Al-Li-Zr alloy containing one or more of 0% Al and the remainder being Al and unavoidable impurities.
すなわち、侵入型元素であるＢ、Ｃ，Ｎ、Ｐ。That is, B, C, N, and P are interstitial elements.
Ｓを添加することにより、これらの原子を粒界に微量偏
析させ、粒界の結合環境を変化させることにより、粒界
破壊が起こらなくなることを見出だし、本発明を完成し
た。すなわち、従来のＡｌ−Ｌｉ合金の粒界近傍に起こ
っていたＬｉ−Ｌｉ。The present invention was completed based on the discovery that adding S causes these atoms to segregate in small amounts at the grain boundaries, thereby changing the bonding environment of the grain boundaries, thereby preventing grain boundary destruction. That is, Li-Li occurs near the grain boundaries of conventional Al-Li alloys.
Ｌｉ−Ｎａ、Ｎａ−Ａｌなどの結合を、侵入型元素であ
るＢ、Ｃ，Ｎ、Ｐ、Ｓを添加することにより、Ｌｉ−Ｘ
−Ｌｉ （Ｘ＝Ｂ、Ｃ，Ｎ、Ｐ、Ｓ以下同様） 、Ｌ
ｉ −Ｘ−ＮａＳＮａ−Ｘ−Ａ Ｉの結合に変化させ
ることにより、粒界の結合力を強化し、全体として強度
および延性を増大させるものである。By adding interstitial elements B, C, N, P, and S to bonds such as Li-Na and Na-Al, Li-X
-Li (X=B, C, N, P, S and so on), L
By changing the bond to i -X-NaSNa-X-A I, the bonding force at grain boundaries is strengthened, and the overall strength and ductility are increased.
次に合金成分を限定した理由について説明する。 Next, the reason for limiting the alloy components will be explained.
Ｌｉ
Ｌｉは、合金材料の強度向上と軽量化に効果がある。こ
の効果は、１．０％より少ないと得られず、４．０％を
越えると熱間加工性が低下する。Li Li is effective in improving the strength and reducing the weight of alloy materials. This effect cannot be obtained if the content is less than 1.0%, and if it exceeds 4.0%, hot workability decreases.
Ｚｒ
Ｚｒは、合金材料の再結晶を抑制するために０．０１〜
０．２０％含有させる。０．０１％より少ないと最終焼
鈍で再結晶が容易に生じ、下部組織を安定化させること
が困難となり、高強度が得られなくなる。また、０．２
０％を越えると鋳造時巨大化合物を晶出しやすくなり、
熱間加工性が劣化する。Zr Zr is 0.01 to 0.01 to suppress recrystallization of the alloy material.
Contain 0.20%. If it is less than 0.01%, recrystallization will easily occur during final annealing, making it difficult to stabilize the underlying structure and making it impossible to obtain high strength. Also, 0.2
If it exceeds 0%, giant compounds will tend to crystallize during casting,
Hot workability deteriorates.
Ｂ、Ｃ，Ｎ、Ｐ、Ｓ
Ｂ、Ｃ，Ｎ、Ｐ、Ｓは、これらの原子を粒界に微量偏析
させ、粒界の結合環境を変化させ、粒界破壊を防止し、
強度および延性を増大させる。B, C, N, P, S B, C, N, P, and S segregate small amounts of these atoms at grain boundaries, change the bonding environment of grain boundaries, and prevent grain boundary fracture.
Increases strength and ductility.
下限値未満および上限を越えると、これらの効果が認め
られない。Below the lower limit and above the upper limit, these effects will not be observed.
また、これらの成分を複数添加する場合は、これらの和
が０．０１〜１％とする。これら成分を複数添加すると
、粒界に競合偏析し、単独添加と同様な結合環境の変化
をもたらし、強度および延性を増大させる。下限値未満
および上限値を越えると、これらの効果が得られなくな
る。Further, when a plurality of these components are added, the sum of these components is 0.01 to 1%. When a plurality of these components are added, competitive segregation occurs at the grain boundaries, resulting in a change in the bonding environment similar to when a single component is added, increasing strength and ductility. If it is less than the lower limit or exceeds the upper limit, these effects cannot be obtained.
ＣおよびＮを除く第１表に示す合金を溶解し、アルゴン
ガスアトマイズ法により急冷凝固粉末を得た。このとき
の冷却速度は、１０３〜１０≠’Ｃ／ｓｅｃであつ−た
。得られた粉末を１４９μｍ以下に分級した。Ｃ，Ｎの
元素を含有しない材料は、上記粉末をそのまま冷間金型
圧縮により直径６３ｍｍ長さ１５０ｍｍの圧粉体（相対
密度約７０％）を作成した。また、Ｃ，Ｎを含有する材
料は、１μｍ以°下のグラファイトまたはＡｌＮ粉末を
上記粉末に加え、高エネルギーミルにより５〜１０時間
混合した後、冷間金型圧縮により直径６３ｒｒｒｍ長さ
１５０ｍｍの圧粉体を作成した。この圧粉体をアルミニ
ウム缶に入れ真空 （１０−１２
〜１０ Ｔｏｒｒ）に引きながら、４５０℃に加熱し
て脱ガスを行いアルミニウム缶を封じた。その後４３０
℃で間接押出により、断面が厚さ１０ｍｍ、幅５０ｍｍ
の板材を得た。これを５００℃で均質化処理した後、熱
間圧延および冷間圧延を行い、厚さ１ｍｍの試験材を得
た。得られた材料から圧延方向と平行にＪＩＳ−１３Ｂ
号引張試験片を採取し、室温で引張試験を行った。それ
らの結果を第１表に示す。The alloys shown in Table 1 except for C and N were melted and rapidly solidified powder was obtained by argon gas atomization. The cooling rate at this time was 103 to 10≠'C/sec. The obtained powder was classified to 149 μm or less. For the material not containing the elements C and N, the powder was directly compressed with a cold mold to form a green compact (relative density about 70%) with a diameter of 63 mm and a length of 150 mm. In addition, materials containing C and N can be prepared by adding graphite or AlN powder of 1 μm or less to the above powder, mixing it in a high-energy mill for 5 to 10 hours, and then pressing it with a cold mold into a material with a diameter of 63rrrm and a length of 150mm. A green compact was created. This green compact was placed in an aluminum can and heated to 450° C. while being vacuumed (10 −12 to 10 Torr) to degas, and the aluminum can was sealed. then 430
By indirect extrusion at ℃, the cross section becomes 10 mm thick and 50 mm wide.
The board material was obtained. After homogenizing this at 500°C, hot rolling and cold rolling were performed to obtain a test material with a thickness of 1 mm. JIS-13B parallel to the rolling direction from the obtained material
A No. 1 tensile test piece was taken and a tensile test was conducted at room temperature. The results are shown in Table 1.
これらの結果から、本発明合金であるＮｏ、１〜４２は
、いずれも破断伸びが１２％以上を有する。From these results, alloys Nos. 1 to 42 of the present invention all have elongations at break of 12% or more.
これに対して、比較例のＮｏ、４３は、Ｂ、Ｃ。On the other hand, Comparative Example No. 43 has B and C.
Ｎ、Ｐ、Ｓのいずれをも含有しないので、破断伸びが４
％と低くなった。Since it does not contain any of N, P, or S, the elongation at break is 4.
%.
Ｎｏ、４４および４５は、Ｓ含有量が１．５０％および
２．００％と高く、破断伸びが８％および６％と低くな
った。Nos. 44 and 45 had high S contents of 1.50% and 2.00%, and low elongations at break of 8% and 6%.
Ｎｏ、４６および４７は、Ｃ含有量が１．５０％および
２．００％と高く、破断伸びが８％および５％と低くな
った。Nos. 46 and 47 had high C contents of 1.50% and 2.00%, and low elongations at break of 8% and 5%.
Ｎｏ、４８および４９は、Ｎ含有量が１．３０％および
２．００％と高く、破断伸びが７％および４％と低くな
った。In Nos. 48 and 49, the N content was high at 1.30% and 2.00%, and the elongation at break was low at 7% and 4%.
Ｎｏ、５０および５１は、Ｐ含有量が１．６０％および
２．５０％と高く、破断伸びが６％および５％と低くな
った。Nos. 50 and 51 had high P contents of 1.60% and 2.50%, and low elongations at break of 6% and 5%.
Ｎｏ、５２および５３は、Ｓ含有量が１．２０％および
３．００％と高く、破断伸びがいずれも５％と低くなっ
た。No. 52 and No. 53 had a high S content of 1.20% and 3.00%, and a low elongation at break of 5%.
Ｎｏ、５４および５５は、（Ｂ＋Ｃ）の含有量が（０，
７５％＋０．６５％）ならびに（１，１０％＋０．８０
％）と、両者の添加量の和が１．０％よりも高く、破断
伸びは、７％および６％とそれぞれ低くなった。No. 54 and 55 have a (B+C) content of (0,
75% + 0.65%) and (1,10% + 0.80
%) and the sum of both addition amounts was higher than 1.0%, and the elongation at break was low at 7% and 6%, respectively.
Ｎｏ、５６および５７は、（Ｂ＋Ｎ）の含有量が（１，
３５％＋１，１０％）ならびに（０，８５％＋２．１３
％）と、両者の添加量の和が１．０％よりも高く、破断
伸びは、５％および３％とそれぞれ低くなった。Nos. 56 and 57 have (B+N) content of (1,
35% + 1,10%) and (0,85% + 2,13
%) and the sum of both addition amounts was higher than 1.0%, and the elongation at break was low at 5% and 3%, respectively.
Ｎｏ、５８および５９は、（Ｂ＋Ｐ）の含有量が（０，
７１％＋０．８２％）ならびに（１，２４％＋０．６３
％）と、両者の添加量の和が１．０％よりも高く、破断
伸びは、４％および３％とそれぞれ低くなった。No. 58 and 59 have (B+P) content of (0,
71% + 0.82%) and (1,24% + 0.63
%) and the sum of the added amounts of both were higher than 1.0%, and the elongation at break was low at 4% and 3%, respectively.
Ｎｏ、６０および６１は、（Ｂ＋Ｓ） の含有量が（１
，０５％＋０．５５％）ならびに（０，８０％＋１．１
５％）と、両者の添加量の和が１．０％よりも高く、破
断伸びは、５％および３％とそれぞれ低くなった。No. 60 and 61 have (B+S) content of (1
,05%+0.55%) and (0,80%+1.1
5%), the sum of the amounts added of both was higher than 1.0%, and the elongation at break was low at 5% and 3%, respectively.
Ｎｏ、６２および６３は、（Ｃ＋Ｎ）の含有量が（０，
８６％＋０．７５％）ならびに（１，１９％＋０．６７
％）と、両者の添加量の和が１．０％よりも高く、破断
伸びは、８％および６％とそれぞれ低くなった。No. 62 and 63 have (C+N) content of (0,
86% + 0.75%) and (1,19% + 0.67
%) and the sum of the added amounts of both were higher than 1.0%, and the elongation at break was low at 8% and 6%, respectively.
Ｎｏ、６４および６５は、（ｃ＋ｐ）の含有量が（０，
７８％＋０．９６％）ならびに（１，６０％＋１．０５
％）と、両者の添加量の和が１．０％よりも高（、破断
伸びは、４％および３％とそれぞれ低くなった。No. 64 and 65 have (c+p) content of (0,
78% + 0.96%) and (1,60% + 1.05
%) and the sum of the amounts added of both was higher than 1.0% (the elongation at break was lower at 4% and 3%, respectively).
Ｎｏ、６６および６７は、（Ｃ＋Ｓ）の含有量が（０，
６８％＋０．９４％）ならびに（１，５４％＋１．５０
％）と、両者の添加量の和が１．０％よりも高く、破断
伸びは、いずれも４％と低くなった。No. 66 and 67 have a (C+S) content of (0,
68% + 0.94%) and (1,54% + 1.50
%) and the sum of the amounts added of both was higher than 1.0%, and the elongation at break was low at 4% in both cases.
Ｎｏ、６８および６９は、（Ｎ＋Ｐ）＋７）含有量が（
０，６９％＋０．７８％）ならびに（０，９５％＋１．
５０％）と、両者の添加量の和が１．０％よりも高く、
破断伸びは、４％および３％とそれぞれ低くなった。No. 68 and 69 have (N+P)+7) content (
0.69%+0.78%) and (0.95%+1.
50%), and the sum of the amounts added of both is higher than 1.0%,
The elongation at break was low at 4% and 3%, respectively.
Ｎｏ、７０および７１は、（Ｎ＋Ｓ）の含有量が（０，
７５％＋１．１２％）ならびに（１，５２％＋０．８５
％）と、両者の添加量の和が１．０％よりも高く、破断
伸びは、４％および３％とそれぞれ低くなった。No. 70 and 71 have (N+S) content of (0,
75% + 1.12%) and (1,52% + 0.85
%) and the sum of the added amounts of both were higher than 1.0%, and the elongation at break was low at 4% and 3%, respectively.
本発明は、以上説明したとおりの構成であって、Ａｌ−
Ｌｉ−Ｚｒ合金に、Ｂ、Ｃ，Ｎ、Ｐ。The present invention has the configuration as explained above, and has an Al-
B, C, N, P in Li-Zr alloy.
Ｓを添加することにより、従来の高強度Ａｉ合金材料よ
りも軽量、かつ高弾性率を有するＡｌ−Ｌｉ合金が得ら
れ、航空機用材料として使用することが可能となった。By adding S, an Al-Li alloy that is lighter and has a higher elastic modulus than conventional high-strength Al alloy materials can be obtained, making it possible to use it as an aircraft material.
Claims (1)
上を含有し、残部Ａｌおよび不可避的不純物からなるこ
とを特徴とする高延性Ａｌ−Ｌｉ合金。[Claims] Li: 1.00 to 4.00% (wt%, the same applies below) Zr: 0.01 to 0.20% and B: 0.002 to 1.0% C: 0.01 to 1.0% N: 0.01 to 1.0% P: 0.001 to 1.0% S: Contains one or more of 0.001 to 1.0%, the balance being Al and unavoidable A highly ductile Al-Li alloy characterized by comprising impurities.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14301089A JPH0310040A (en) | 1989-06-07 | 1989-06-07 | High ductility al-li-zr alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14301089A JPH0310040A (en) | 1989-06-07 | 1989-06-07 | High ductility al-li-zr alloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0310040A true JPH0310040A (en) | 1991-01-17 |
Family
ID=15328850
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14301089A Pending JPH0310040A (en) | 1989-06-07 | 1989-06-07 | High ductility al-li-zr alloy |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0310040A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170306761A1 (en) * | 2014-11-25 | 2017-10-26 | Mitsubishi Heavy Industries, Ltd. | Impeller and rotary machine |
| US10655634B2 (en) | 2017-06-30 | 2020-05-19 | Borgwarner Inc. | Multi-piece compressor wheel |
-
1989
- 1989-06-07 JP JP14301089A patent/JPH0310040A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170306761A1 (en) * | 2014-11-25 | 2017-10-26 | Mitsubishi Heavy Industries, Ltd. | Impeller and rotary machine |
| US10655470B2 (en) * | 2014-11-25 | 2020-05-19 | Mitsubishi Heavy Industries, Ltd. | Impeller and rotary machine |
| US10655634B2 (en) | 2017-06-30 | 2020-05-19 | Borgwarner Inc. | Multi-piece compressor wheel |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2109835C1 (en) | Low-density aluminum-based alloy and material of manufacturing product therefrom | |
| US6139653A (en) | Aluminum-magnesium-scandium alloys with zinc and copper | |
| JP2730847B2 (en) | Magnesium alloy for castings with excellent high temperature creep strength | |
| EP0642598B1 (en) | Low density, high strength al-li alloy having high toughness at elevated temperatures | |
| NZ205764A (en) | Aluminium alloys containing lithium,magnesium and zinc and uses thereof | |
| JP3278232B2 (en) | Lightweight high strength magnesium alloy for casting | |
| JPH01255632A (en) | Ti-al intermetallic compound-type alloy having toughness at ordinary temperature | |
| JPH06279905A (en) | Superplastic magnesium alloy | |
| JPH0310040A (en) | High ductility al-li-zr alloy | |
| JPS63312901A (en) | Heat resistant high tensile al alloy powder and composite ceramics reinforced heat resistant al alloy material using said powder | |
| US2596486A (en) | Titanium-base alloys | |
| JPH01272743A (en) | High tensile aluminum alloy having excellent heat resistance | |
| JPH0218374B2 (en) | ||
| JP3387548B2 (en) | Manufacturing method of magnesium alloy molded product | |
| US3157496A (en) | Magnesium base alloy containing small amounts of rare earth metal | |
| JPH032218B2 (en) | ||
| JPH0432535A (en) | High strength and high rigidity magnesium-lithium alloy | |
| JP2711296B2 (en) | Heat resistant aluminum alloy | |
| JPH0665668A (en) | Superplastic magnesium alloy | |
| JP2768676B2 (en) | Lithium-containing aluminum alloy produced by rapid solidification route | |
| JP2604663B2 (en) | Lightweight high strength magnesium alloy | |
| JPH0379738A (en) | High strength al alloy material | |
| JPS6311643A (en) | High strength aluminum alloy having superior heat resistance | |
| JPH01290738A (en) | Aluminum alloy having excellent heat resistance | |
| JPH02258943A (en) | High strength and high ductility al-be-li-cu-mg alloy |