JPS62142752A - Heat treatment of lithium-containing aluminum alloy - Google Patents
Heat treatment of lithium-containing aluminum alloyInfo
- Publication number
- JPS62142752A JPS62142752A JP61283024A JP28302486A JPS62142752A JP S62142752 A JPS62142752 A JP S62142752A JP 61283024 A JP61283024 A JP 61283024A JP 28302486 A JP28302486 A JP 28302486A JP S62142752 A JPS62142752 A JP S62142752A
- Authority
- JP
- Japan
- Prior art keywords
- alloy
- aluminum
- heat treatment
- less
- hours
- 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
Classifications
-
- 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
- C22F1/047—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 magnesium as the next major constituent
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Organic Chemistry (AREA)
- Crystallography & Structural Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Physics & Mathematics (AREA)
- Metallurgy (AREA)
- Thermal Sciences (AREA)
- Battery Electrode And Active Subsutance (AREA)
- Heat Treatment Of Steel (AREA)
- Secondary Cells (AREA)
- Chemical Treatment Of Metals (AREA)
- Preventing Corrosion Or Incrustation Of Metals (AREA)
- Analysing Materials By The Use Of Radiation (AREA)
Abstract
Description
【発明の詳細な説明】
本発明は、過小焼なまし処理ににつてｌ−ｉ金石Ａｇ合
金の剥１ｉ１１１＋ｌｉ！食（ｅｘｒｏｌｉａｔｉｏｎ
Ｃ０ｒｌ’Ｏ８！Ｏｎ ）に対する感度を低下さける
と同＋１．’ｊに、大きな機械的耐性と十分な耐損傷性
とを１ｑるための方法に係わる。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to under-annealing treatment of l-i goldstone-Ag alloy. food (exroliation)
C0rl'O8! If you avoid reducing the sensitivity to ), the same +1. It concerns a method for providing high mechanical resistance and sufficient damage resistance to 'j.
周知のにうに、大きな耐食性を得ることは、アルミニウ
ム合金特に航空用アルミニウム合金の開発にＪ３ける重
要な問題の１つである。高耐食性は通常１スデツブ又は
２スアツブの過剰焼４ｋまし熱処理（例えば八ｌｕｍｉ
ｎｕｍ Ａｓ５ｏｃｉａｔｉｏｎの規定によるΔｊ 、
Ｚｎ、 Ｃｕ、ＭＯ合金）１７３処理）ニヨッて得られ
る。この十二分な焼なましによる耐食性増加操作は、−
・般的に高温（Ｔと１９０℃＞ −Ｃ十分に長い時間の
間燃なましを行なうことによって大きな耐食性が得られ
るとされているアルミニウムーリチウム合金にも適用で
きる。As is well known, obtaining high corrosion resistance is one of the important issues in the development of aluminum alloys, particularly aircraft aluminum alloys. High corrosion resistance is usually achieved by 4k annealing heat treatment of 1 or 2 steps (e.g. 8 lumi).
Δj according to the regulations of num As5ocation,
Zn, Cu, MO alloy) 173 treatment). This corrosion resistance increasing operation by sufficient annealing is -
- It can also be applied to aluminum-lithium alloys, which are generally said to have great corrosion resistance by annealing them at high temperatures (T and 190°C > -C for a sufficiently long period of time).
しかしながら従来のΔｇ合金に関して１９られる機械的
強さと耐損傷性との間の最適バランスは、耐食性増加効
果を右する前述の如き過剰焼なまし処理では１−１られ
へい。However, the optimum balance between mechanical strength and damage resistance found for conventional Δg alloys cannot be compromised by excessive annealing treatments such as those described above, which provide a corrosion resistance enhancing effect.
従来の）ｌルミニウム合金では、機械的強さと耐食性と
の間の最適バランス及び機械的強さと削Ｌ）（Ｕ性どの
間の最適バランスは、異なる合金にＪ３いて、且つ異な
る熱処理を行なうことによってしかｊヱ成されていない
。In conventional aluminum alloys, the optimum balance between mechanical strength and corrosion resistance and the optimum balance between mechanical strength and machinability can be achieved by using different alloys and subjecting them to different heat treatments. Only a few things have been completed.
一例として、引張り疲労応力を最６多く受ける部分に使
用される合金２０２４ （八ｌｕｍｉｎｉｕｍ Ａｓ５
ｏｃｉｌ′ｌ−１Ｏｎに規定）は最適の機械的強ざ−疲
れ強さバランスを示す。しかしながらこの合金はＴ４又
はＴ３の状態で使用される。即ら室温で１１．’ｊ効（
ａｇｉｎｇ）化されるため、製品の厚みが数ミリメート
ルを越える場合には十分な耐薄片剥脱腐食性（ｆｌａｋ
ｉｎｇｃｏｒｒｏｓｉｏｎ）を示さない。As an example, alloy 2024 (8luminium As5
ocil'l-1On) indicates the optimum mechanical strength-fatigue strength balance. However, this alloy is used in the T4 or T3 state. That is, at room temperature 11. 'j effect (
aging), so if the thickness of the product is more than a few millimeters, it has sufficient flaking corrosion resistance (flake corrosion resistance).
ingcorrosion).
自然雰囲気下での耐薄片剥脱腐食性を測定するには、薄
片剥脱腐食テストに関するＥＸＣＯ（ＡＳＴＭＧ ３４
−１９７９規格）を９６時間行なうとＪ、いことが判明
した。実際、ＥＸＣＯＸＣ上にかりた試料と海浜のにう
な雰囲気に晒した試料との比較からｌ−ｉ含有ΔＱ合舎
の場合には材料の耐食性が種々の処理を用いると豆いに
同程度であることが知見される。但しＥＸＣＯＸＣ上の
方が自然腐食よりやや強い腐食作用を示す。尚、ＥＸＣ
Ｏテストの結果はレベルに応じて下記の如く表記される
（前出の規格による）。To determine flake corrosion resistance in natural atmosphere, use the EXCO (ASTMG 34) for flake corrosion test.
-1979 standard) for 96 hours, it was found that J. In fact, a comparison between a sample placed on EXCOXC and a sample exposed to a seashore atmosphere shows that in the case of l-i-containing ΔQ joints, the corrosion resistance of the material is comparable to that of beans when various treatments are used. It is found that However, the corrosion effect on EXCOXC is slightly stronger than that of natural corrosion. Furthermore, EXC
The results of the O test are expressed as follows depending on the level (according to the standards mentioned above).
ＥＡ 軽いＡり片剥脱腐食 この表記は７１準試料との比較によって行／、１つ。EA Light A flake corrosion This notation is based on the comparison with 71 quasi-samples.
本発明では焼なましをＦ記の温度及び時間範囲で実施し
なければならない。In the present invention, annealing must be carried out within the temperature and time ranges listed in F.
ｔ ＞ ２０Ｘ ５ ｅＸＤ （（１５０−Ｔ ）／
３０） ”ｔ ＜ ８０ｘ ５ ｅｘｐ （（１５０
−Ｔ ）／３０） 本及び
ＭＣＪ≧２％の場合 Ｔ≦１６０℃
１≦Ｍａ≦２％の場合
Ｔ丘１６０℃−５×（２−％Ｍｑ）’ＣＭ ＣＪ≦１％
の場合 Ｔ≦１５５℃
但し を二時効処理１１．１間（ｊｉｌｔ位：時）Ｔ：
時効処理温度（１１１位；℃）
本ｅｘｐはベキ指数即ら累乗を意味する。t > 20X 5 eXD ((150-T)/
30) ”t < 80x 5 exp ((150
-T)/30) When MCJ≧2% T≦160℃ When 1≦Ma≦2% T hill 160℃-5×(2-%Mq)'CM CJ≦1%
In the case of T≦155℃, however, two aging treatment 11.1 hours (jilt position: hours) T:
Aging treatment temperature (111th place; °C) This exp means a power exponent, that is, a power.
時効処理【よ好ましくは１５５℃以下の温度及び／又は
２４Ｘ ５ ｅＸｌｌ （（１５０−Ｔ ）／３０）
Ｊ：すｉ ０１１．５間（単位二時）で行なう。温度
Ｔの単位ｔま℃て・ある。Aging treatment [preferably at a temperature of 155°C or less and/or 24X 5 eXll ((150-T)/30)
J: Sui 011.5 (unit: 2 o'clock). The unit of temperature T is t.
このＪ、うに処理した合金はＥＸＣＯデス１〜にス・１
してＢ以下の感度を示づ。これは自然雰囲気て゛の良り
Ｔな性状、少＜ｒ ＜とム２０２４ （状態−「３又は
Ｔ４１に匹敵する機械的強さ及び十分な耐損傷性に該当
する。This J, sea urchin treated alloy is
The sensitivity is below B. This corresponds to good properties in a natural atmosphere, mechanical strength comparable to condition 3 or T41, and sufficient damage resistance.
１１４間が２０ｘ ５ ｅｘｐ （（１５０−Ｔ ）
／３０ ） Ｊ、り短いと十分な機械的強さが１９ら
れない。８０ｘ５ ｅｘｐ（（１５０−Ｔ ）／３０）
を越える処理時間では強靭性が最高限度を越え■つ靭性
が若しく低Ｔ” ｔＪ’る。114 is 20x 5 exp ((150-T)
/30) If the length is too short, sufficient mechanical strength will not be achieved. 80x5 exp ((150-T)/30)
If the treatment time exceeds 100%, the toughness exceeds the maximum limit and the toughness becomes low.
温度を前記値より高くすると耐刷ｍ＋ｒｉ、食性が不十
分になる。If the temperature is higher than the above value, printing durability (m+ri) and edibility will become insufficient.
本発明は特に、ｆｆｌｆｆｉ％で１〜４％のｌｉ；
０〜５％のＣＵ； ０〜７％のＭＯ：Ｏ〜０．２％のＺ
ｒ；０〜０．４％のＣｒ： ０〜１％の１ｙｌｎ；Ｆｅ
＜０．５％；ＳｉＳ２．５％；及び他の元素例えばＨｆ
。The present invention particularly provides 1 to 4% li in fffffi%;
0-5% CU; 0-7% MO: O-0.2% Z
r; 0-0.4% Cr: 0-1% yln; Fe
<0.5%;SiS2.5%; and other elements such as Hf
.
Ｎｂ、Ｖ、Ｗ、Ｔａ、Ｔ ｉを各々０．５％未満含み、
残りがアルミニウムと通常の不純物であるにうなアルミ
ニウムーリヂウム合金に適用される。Containing less than 0.5% of each of Nb, V, W, Ta, and Ti,
Applies to aluminum-ridium alloys where the remainder is aluminum and normal impurities.
この種の合金はインゴット冶金術又は高速凝固法（粉末
冶金、「スプラット冷却」、ストリップの高速凝固等）
によって製造覆ることかできる。This type of alloy can be manufactured using ingot metallurgy or fast solidification methods (powder metallurgy, "splat cooling", fast solidification of strips, etc.)
Can be covered by manufacturing.
これらの製品はリチウム金石合金の場合に通常使用され
る方法によって変形させられ、熱間及び／又は冷間加１
にかけられ、次いで固溶化処理され、急冷操作を受Ｃノ
、その後任意に冷間加工され、Ｗ＃造内的析出加熱処理
かけられる。These products are deformed by methods commonly used for lithium goldstone alloys, including hot and/or cold working.
It is then solution treated, subjected to a quenching operation, then optionally cold worked and subjected to a W# internal precipitation heat treatment.
本発明はあらゆる形態の製品（鍛造、ダイスクンピング
、圧延、押出し延伸等による製品）の他、鍛圧には全く
かけられないキセスト合金にｂ使用される。The present invention is applicable to all types of products (products produced by forging, die-scanning, rolling, extrusion-stretching, etc.) as well as to xist alloys that cannot be subjected to forging pressure at all.
以下、添付図面を参照しながら実施例を挙げて本発明を
より詳細に説明する。尚、特にの％は重量％であるもの
とする。Hereinafter, the present invention will be described in more detail by way of examples with reference to the accompanying drawings. In addition, especially % shall be weight %.
友直■ユ
この実施例１は先行技術に係わり、過剰時効処理したΔ
ｇ−１−ｉ合金試料に対する実際の大気中でのテストと
ＥＸＣＯＸＣ上との間の相似性を示すものである。Tomonao■Yu This Example 1 is related to the prior art, and the Δ
Figure 2 shows the similarity between actual atmospheric testing and on EXCOXC for g-1-i alloy samples.
１ｉ２．７％、Ｃｕ １．３％、ＭＯ１％、Ｚｒ０９
１１％、Ｆｅ０．０４％、３ｉ０．０３％、残りアルミ
ニウムを含む合金８０９０をφ２００Ｍのビレッ１〜状
に：ｐ ＋！スト成形し、５３３℃で２４時間均質化し
、φ１４０１醐まで削り、４３０℃で１００Ｘ１３ａ＊
２のシー１〜バ〜に押出しく押出し率ユ１２）、５３５
℃で１時間３０分固溶化処理し、冷水で急冷し、２％の
引張ストレッチングにかけ、その復極々の時効処理にか
りた。1i2.7%, Cu 1.3%, MO1%, Zr09
Alloy 8090 containing 11% Fe, 0.04% Fe, 0.03% 3i, and the rest aluminum is shaped into a φ200M billet: p +! Strain molded, homogenized at 533℃ for 24 hours, ground to φ1401, 100X13a* at 430℃
Extrusion rate 12), 535
It was subjected to solid solution treatment at ℃ for 1 hour and 30 minutes, quenched with cold water, subjected to 2% tensile stretching, and then subjected to aging treatment.
同様にして、１−ｉ２．０％、Ｃｕ２．１％、Ｍ（Ｊｌ
、４％、Ｚｒ０．１１％、Ｆｃ０．０４％、３ｉ０．０
３％、残りアルミニウムからなる合金２０９１をφ ２
００＃のビレット状に：１−１ｔスト成形し、 ５２５
℃で２４時間均質化処理し、φ １４０ ａｍまで削り
、前述の条件で押出し成形し、５２６℃で１１１５間３
０分固溶化処理し、冷水で急冷し、２％の引張りス１−
レッチングにか（〕、その後１１￥効処理にかりた。Similarly, 1-i2.0%, Cu2.1%, M(Jl
, 4%, Zr0.11%, Fc0.04%, 3i0.0
Alloy 2091 consisting of 3% aluminum and the remaining aluminum is φ2
00# billet shape: 1-1t stroke molding, 525
Homogenized at 526°C for 24 hours, ground to φ 140 am, extruded under the above conditions, and heated at 526°C for 1115 minutes.
Solution treatment for 0 minutes, quenching with cold water, 2% tensile stress 1-
After that, it took 11 yen for retching.
合金２０２４Ｔ ３５１からなる断面１００Ｘ １３の
シー１〜バーを基準試料とする。Sea 1 to bar made of alloy 2024T 351 and having a cross section of 100×13 are used as reference samples.
時効処理した押出しシートバー試料を切削加工して梗み
を幅の半分に亘って １／２にし、粗い押出し表面状態
と切削加工した表面とを同時に右りるＪ：うにした。The aged extruded sheet bar sample was machined to reduce the curvature by half over half the width, and the rough extruded surface condition and the machined surface were simultaneously polished.
次いでこれらの試料を下記の条件で剥因１朋食テス１〜
と、仏国カマルグにあるＳ、１ｌｌｉｎＳ ｄａ Ｇｉ
ｒａｕｄステーションでの海浜環境におＧ−Ｊる人気露
出とにかけた。Next, these samples were subjected to peeling test 1 under the following conditions.
and S, 1llin S da Gi in Camargue, France.
G-J's popular exposure to the beach environment at RAUD station.
一アセントン又はアルコールでの脱脂処理１りに絶縁性
部材によってラックに固定した２００Ｘ １００１繍２
のプレート
一検査前の露出時間：２２ケ月
比較結果は次の通りである。200X 1001 embroidery fixed to the rack with insulating material after degreasing with Ascenton or alcohol 1
The results of the comparison of the exposure time of the plates before the test: 22 months are as follows.
ｌ ｉ ２．０％、Ｑｕ １．９％、Ｍｇ１．６％
、ＺｒＯ，０８％、ｐｅｏ、０５％、Ｓｉ０．０４％、
残りアルミニウムから′よる組成の合金２０９１を断面
８００×３００ｍｍ２、中量１．５１−ンのプレー１〜
状にキ１１ス１〜成形し、５２６℃で２４時間均質化処
理し、削り処理して先端を切落しくプレートの厚み：
２７０ｍｍ）、４７０℃で１２時旧聞加熱し、この温
度から厚みが３、２ｍになるまで熱間圧延にかり、リー
ル状に巻き上げ、４５０℃で１時間焼なまし処１！Ｉ！
ｔ、、 １．Ｇｍｎまで連続冷間圧延処理し、５２６
℃で２０分間固溶化処理し、冷水で急冷を行ないその後
時効処１！１１にかけた。薄片剥＋１！２腐食、引張り
に関する機械的ＩＳ＋ １１及び児ＩＩ）靭性（ＫＣＡ
）に関づるテストの結果は次の通りである。l i 2.0%, Qu 1.9%, Mg 1.6%
, ZrO, 08%, peo, 05%, Si0.04%,
From the remaining aluminum, alloy 2091 with a composition according to
The plate was formed into a 11-kiss shape, homogenized at 526°C for 24 hours, and shaved to cut off the tip.Thickness of the plate:
270mm), heated at 470℃ for 12 hours, hot rolled from this temperature until the thickness reached 3.2m, wound into a reel, and annealed at 450℃ for 1 hour. I!
t,, 1. Continuously cold rolled to Gmn, 526
Solution treatment was carried out at ℃ for 20 minutes, quenched with cold water, and then subjected to aging treatment 1!11. Flaking+1!2 Mechanical IS+ for corrosion, tensile 11 and II) Toughness (KCA
) test results are as follows.
１５０℃で４８時間時効処理した合金２０９１試利と状
態Ｔ３５１の合金２０２４とを、幅１００１Ｍの正弦曲
線荷車ｅ５＝９０＋−４０ＭＰａ （中央亀裂を有す
る試験片）下での疲労亀裂伝搬に対する抵抗性に関して
比較し ノご 。Alloy 2091 samples aged at 150°C for 48 hours and Alloy 2024 in condition T351 were tested for resistance to fatigue crack propagation under a sinusoidal cart of width 1001M e = 90+-40MPa (specimen with central crack). Compare.
第１図はこれら２種類の合金に関して、シートの長手方
向と横方向との聞の種々の方向におけるナイクル数＜Ｎ
）対亀裂長さく２ａ）の関係を示１種々の曲線の範囲を
示している。このグラフから明らかなＪ：うに前記２種
類の合金は互いにほぼ同等の性質を示すが、サイクル数
が多くなると２０９１の方が２０２４Ｊ：り優れた挙動
を示し、結果のバラつきも２０９１の方が少ない。Figure 1 shows the Nykle number <N in various directions between the longitudinal and lateral directions of the sheet for these two types of alloys.
) shows the relationship between crack length and crack length 2a) 1 shows the range of the various curves; It is clear from this graph that the above two types of alloys have almost the same properties, but when the number of cycles increases, 2091 shows better behavior than 2024J: and the variation in the results is smaller for 2091. .
実施例３
１ｉ２．５％、Ｃｕ４１．４％、ＭＯｏ、９５％、Ｚｒ
Ｏ，０６％、ｌ：ｅｏ、０６％、３ｉ０．０３％、残り
アルミニウムからなる組成の合金８０９０を断面８００
Ｘ３００ ｓ２、ｍｆｆ１１．５＋−ンのプレート状に
キャスト成形し、５３５℃で２４時間均質化処理し、先
端を切落し、厚み２７０ 、馴まで削り、４５０℃で１
２時間再加熱し、４５０℃の温度から３．２ｍｍの厚さ
まで熱間圧延にか（）、４５０℃で１時間焼なまし処理
し、低温条件で９さ１，６Ｍまでシー！・状に圧延し、
５３５℃で２０分開国溶化処理し、冷水で急冷し、１．
５％の冷間引張りストレッヂングにかけ、下記表３に記
載の条件で時効処理した。ＥＸＣＯＸＣ上と、自然の海
浜雰囲気下でのテストと、引張り強さ及び靭性（ＫＩＣ
）に関する機械的特性のテストとの結果を合金２０２４
Ｔ ３５１と比較して表３に示ず。Example 3 1i2.5%, Cu41.4%, MOo, 95%, Zr
Cross section 800 of alloy 8090 with a composition consisting of O, 06%, l:eo, 06%, 3i 0.03%, and the remainder aluminum.
It was cast into a plate shape of
Reheated for 2 hours, then hot rolled from a temperature of 450℃ to a thickness of 3.2mm (), annealed at 450℃ for 1 hour, and then rolled to a thickness of 9mm to 1.6mm under low temperature conditions.・Rolled into shape,
After 20 minutes of open country solution treatment at 535°C, quenching with cold water, 1.
It was subjected to 5% cold tensile stretching and aged under the conditions listed in Table 3 below. Tests on EXCOXC and under natural beach atmosphere and tensile strength and toughness (KIC)
) Mechanical property tests and results for Alloy 2024
Not shown in Table 3 in comparison to T 351.
車 幅１００Ｍの試験片
＊率 ｄ ：密度
実」ｉ量しユ
１ｉ２．７％、Ｍｇ１．０％、Ｃｕ１．３％、Ｚｒｏ、
１１ ％、Ｆｅ０．０４％、３ｉ０．０３％、残りアル
ミニムからなる組成の合金をφ２００ ｔｒｒｍのビレ
ット−状に：Ｉ＝ ＋ｐスト成形し、５３５℃で２４時
間均質化処理し１．１ＡＯｎｏまで削り、４３０℃で断
面１００ｘ １３馴２のシートバー形状に熱間１１１１
出し成形し、５３５°Ｃで１時間３０分固溶化処理し、
冷水で急冷し、２％の引張りス１〜レッチングにかけ、
下記表４に示した条件で時効処理した。Car test piece with a width of 100M
An alloy with a composition of 11%, 0.04% Fe, 0.03% 3i, and the rest aluminum was molded into a billet of φ200 trrm: I = +p, homogenized at 535°C for 24 hours, and ground to 1.1AOno. , Hot 1111 to a sheet bar shape with a cross section of 100x 13mm at 430℃
It was molded and solution treated at 535°C for 1 hour and 30 minutes.
Rapidly cool with cold water, apply 2% tensile strength 1 to retching,
Aging treatment was performed under the conditions shown in Table 4 below.
薄片剥脱腐食に関Ｊ°るデス１−（ＥＸＣＯテス１デス
び海８ｔ２ｊ囲気への露出）と靭性（Ｋ［Ｃ）に関する
機械的特性のテストとの結果を合金２０２４と比較して
表４に示ザ。The results of the mechanical property tests for exfoliation corrosion (EXCO test 1 and exposure to ambient air) and toughness (K [C) are compared with alloy 2024 in Table 4. Demonstration.
表 ４
時効処理 厚み１／２し厚み１／２し ｄｔｈ″
長手方向の性状ベルにお べＪしにおり ＩｌＯ
，２１１ｍ 八５．Ｇ５Ｍ〆］；６′ ＫＩＣ／ＬＴ
けるｌ：ＸｃＯ？）自然界１１１１ （）ｌＰ
ａ） （ＨＰａ） ｆＸ） （）ＩＰａｌ’ｍ
）デスＩ〜 気デス１−
１９０℃テ１２時間 ＥＣ−ＥＤ ［Ｂ
４’１０５４０ ７ ３７（ピーク
近傍）
本ＪＬ服
２０２４Ｔ３５１ ＥＤ ［Ｃ−［Ｄ
２．７９ ４００ ５３０ １３
３９本５ａｌｉｎｓｄｃＧｉｒａｕｄ ステーシコ
ンで２２ケ月晒Ｊ０傘＄ｄ：ｆｉＩＫ
実施例５
１ｉ２．０％、ＣＬＪ３．２％、ｔｖｌｏ、３％、Ｚｒ
００１１％、Ｆｅ０．０４％、３ｉ０．０４％、残りア
ルミニウムからなる合金をφ ２００Ｍのごレット状に
キ１７ス１〜成形し、５１０℃で１２時間均質化処Ｊ！
ｌ！ シ更に５２０℃で２４時間均質化処理し、φ １
４０ＩｒＩＭまで削り、４２０℃で断面１０１００Ｘ１
３のシー１〜バー状に押出成形し、５２５℃で１１Ｉ、
ｌＪ間３０分固溶化処理し冷水で急冷し、２％の冷間引
張りス１へレッチングにかけ、本発明に従って １５０
℃で４８時間ａ′ 時効処理した。Table 4 Aging treatment Thickness 1/2 Thickness 1/2 dth''
IlO in the longitudinal direction
, 211m 85. G5M〆];6' KIC/LT
Keru:XcO? )Nature 1111 ()lP
a) (HPa) fX) ()IPal'm
) Death I~ Ki Death 1- 190℃Te 12 hours EC-ED [B
4'10540 7 37 (near the peak) Genuine JL clothes 2024T351 ED [C-[D
2.79 400 530 13
39 pieces 5 alinsdcGiraud J0 umbrella exposed for 22 months with station console $d: fiIK Example 5 1i 2.0%, CLJ 3.2%, tvlo, 3%, Zr
An alloy consisting of 0.0011%, 0.04% Fe, 0.04% 3i, and the remainder aluminum was formed into a 200M φ200M pellet and homogenized at 510°C for 12 hours.
l! The film was further homogenized at 520°C for 24 hours, and φ1
Cut to 40IrIM, cross section 10100X1 at 420℃
3, extrusion molded into a bar shape, heated to 11I at 525°C,
Solution treated for 30 minutes for 1J, quenched with cold water, retched to 2% cold tensile strength 150 according to the present invention
A' aging treatment was performed at ℃ for 48 hours.
艮手力向の引張り強さ及び艮千−横方向の靭性ＫＩＣに
関する機械的特性と、Ｅ Ｘ ＣＯＡＤ片剥脱腐食アス
トの結果と密度ｄとを従来の合金２０２４及び１０７５
と比較して表５に示づ。Mechanical properties in terms of tensile strength in the force direction and toughness in the lateral direction KIC, results of EX COAD exfoliation corrosion ast and density d of conventional alloys 2024 and 1075
A comparison is shown in Table 5.
人−一旦
ＲＯ１２Ｉｔｓ 八（５，ｆｌ＋５４１死Ｄ
ＫＩＣ−ＬＴ ［ＸＣＯｄ（Ｊ／ｃｒｉ”本発
明 ５２５ ＧＯ２１１４４Ｐ−ｔＥＡ ２．
５８５７０６５ＴＧ５１ ５５０ ６０５
１１ ３Ｉ Ｐ−ＥＣ２，８１０２０
２４Ｔ３５１ ４００ ５３０ １３
３９ 「Ｄ ２．７９０Person - Once RO12Its 8 (5, fl + 541 death D
KIC-LT [XCOd(J/cri” Invention 525 GO21144P-tEA 2.
5857065TG51 550 605
11 3I P-EC2, 81020
24T351 400 530 13
39 "D 2.790
第１図は２種類の合金シー１〜の種々の方向における亀
裂長さ対実施サイクル数の関係を丞す曲線グラフである
。
手続補正書
昭和６２年１月７日
１、事件の表示 昭和６１年特許願第２８３０２４号
２、発明の名称 リチウム含有アルミニウム合金の熱
処理方法ラリュミニウム・ペシネ
５、補正命令の日付 自 発
６、補正により増加する発明の数
７、補正の対象 明細書
薄片刊＋１１２１１ｉ＜食に関するデスＩ−（ＥＸＣＯ
テス１デスび１ｍ浜雰囲気への露出）と１刀性（ＫＩＧ
＞に開するｄ域内特性のテストとの結果を合金２０２４
と比較して表４に示す。
ベルにお ベルにおけ ｌ１０．２１１ｍ Ａ
３６５ＳにＩｃ／ＬＴけるＥＸＣＯる自然゛雰囲
（ＨＰａｌ （ｔ４Ｐａｌ （Ｘ） （ＨＰ
ａ汀１９０℃で１２時間 ＥＣ−ＥＤ ＥＢ
４９０５４０ ７ ３７（ピー
ク近傍）
傘Ｓａｌ ｉｎｓ ｄｅ Ｇｉｒａｕｄ ステーショ
ンで２２ケ月晒す。
傘率ｄ：６話度FIG. 1 is a graph of the crack length in various directions versus the number of cycles performed for two types of alloy sheets. Procedural amendment January 7, 1985 1. Indication of case: 1985 Patent Application No. 283024 2. Title of invention: Method for heat treatment of lithium-containing aluminum alloy Laluminium Pecine 5. Date of amendment order: Voluntary 6. By amendment Increasing number of inventions 7, subject of amendment Specification thin paper publication +11211i
Tess 1 death and 1 m beach atmosphere exposure) and 1 sword nature (KIG
> The results of the tests for the characteristics in the d region of Alloy 2024
A comparison is shown in Table 4. At the bell At the bell l10.211m A
EXCO's natural atmosphere with Ic/LT on 365S
(HPal (t4Pal (X) (HPal
a 12 hours at 190℃ EC-ED EB
490540 7 37 (near the peak) Exposure at Sal ins de Giraud station for 22 months. Umbrella rate d: 6 episodes
Claims (4)
ながら耐剥離腐食性を向上させるためのＬｉ含有Ａｌ合
金の熱処理方法であって、最終時効処理を下記の温度Ｔ
（単位℃）及び時間ｔ（単位時）の範囲 ｔ≧２０×５ｅｘｐ（（１５０−Ｔ）／３０）ｔ≦８０
×５ｅｘｐ（（１５０−Ｔ）／３０）但し Ｍｇ≧２％
の場合はＴ≦１６０℃ １≦Ｍｇ≦２％の場合は Ｔ≦１６０℃−５（２−％Ｍｇ）℃ Ｍｇ≦１％の場合はＴ≦１５５℃ で行なうことを特徴とする方法。(1) A heat treatment method for a Li-containing Al alloy to improve exfoliation corrosion resistance while maintaining high mechanical strength and sufficient damage resistance, the final aging treatment being carried out at the following temperature T.
(unit ℃) and time t (unit hour) range t≧20×5exp((150-T)/30)t≦80
×5exp ((150-T)/30) However, Mg≧2%
If T≦160°C, if 1≦Mg≦2%, T≦160°C-5(2-%Mg)°C, and if Mg≦1%, T≦155°C.
／３０）以上であることを特徴とする特許請求の範囲第
１項に記載の方法。(2) The processing time is 24×5exp ((150-T)
/30) or more, the method according to claim 1.
する特許請求の範囲第１項又は第２項に記載の方法。(3) The method according to claim 1 or 2, wherein the treatment temperature is 155°C or lower.
７％未満のＭｇと、０．２％未満のＺｒと、０．４％未
満のＣｒと、１％未満のＭｎとを含み、その他Ｆｅ、Ｓ
ｉ、Ｈｆ、Ｎｂ、Ｖ、Ｗ、Ｔａ及びＴｉを各々０．５％
未満含み、残りがアルミニウム及び通常の不純物である
ような合金への特許請求求の範囲第１項から第３項のい
ずれかに記載の方法の使用。(4) 1 to 4% (by weight) of Li and 1 to 5% of Cu;
Contains less than 7% Mg, less than 0.2% Zr, less than 0.4% Cr, and less than 1% Mn, and other Fe, S
0.5% each of i, Hf, Nb, V, W, Ta and Ti
Use of the method according to any one of claims 1 to 3 on alloys containing less than or equal to 50% aluminum and the remainder being aluminum and normal impurities.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR8518208 | 1985-11-28 | ||
| FR8518208 | 1985-11-28 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62142752A true JPS62142752A (en) | 1987-06-26 |
Family
ID=9325580
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP61283024A Pending JPS62142752A (en) | 1985-11-28 | 1986-11-27 | Heat treatment of lithium-containing aluminum alloy |
Country Status (8)
| Country | Link |
|---|---|
| EP (1) | EP0227563B1 (en) |
| JP (1) | JPS62142752A (en) |
| AT (1) | ATE52109T1 (en) |
| BR (1) | BR8605809A (en) |
| CA (1) | CA1291927C (en) |
| DE (1) | DE3670510D1 (en) |
| ES (1) | ES2014248B3 (en) |
| IL (1) | IL80765A0 (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5462712A (en) * | 1988-08-18 | 1995-10-31 | Martin Marietta Corporation | High strength Al-Cu-Li-Zn-Mg alloys |
| US5259897A (en) * | 1988-08-18 | 1993-11-09 | Martin Marietta Corporation | Ultrahigh strength Al-Cu-Li-Mg alloys |
| US5211910A (en) * | 1990-01-26 | 1993-05-18 | Martin Marietta Corporation | Ultra high strength aluminum-base alloys |
| US5133931A (en) * | 1990-08-28 | 1992-07-28 | Reynolds Metals Company | Lithium aluminum alloy system |
| US5234662A (en) * | 1991-02-15 | 1993-08-10 | Reynolds Metals Company | Low density aluminum lithium alloy |
| DE4113352C2 (en) * | 1991-04-24 | 1996-05-23 | Hoogovens Aluminium Gmbh | Process for the production of aluminum sheets |
| US5198045A (en) * | 1991-05-14 | 1993-03-30 | Reynolds Metals Company | Low density high strength al-li alloy |
| US5240521A (en) * | 1991-07-12 | 1993-08-31 | Inco Alloys International, Inc. | Heat treatment for dispersion strengthened aluminum-base alloy |
| KR940008071B1 (en) * | 1991-12-26 | 1994-09-01 | 한국과학기술연구원 | Heat treatment method of al-li |
| US8118950B2 (en) | 2007-12-04 | 2012-02-21 | Alcoa Inc. | Aluminum-copper-lithium alloys |
| US8333853B2 (en) | 2009-01-16 | 2012-12-18 | Alcoa Inc. | Aging of aluminum alloys for improved combination of fatigue performance and strength |
| FR2945464B1 (en) * | 2009-05-13 | 2012-03-23 | Alcan Rhenalu | PROCESS FOR WELDING ASSEMBLY OF ALUMINUM ALLOY PARTS. |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3483607D1 (en) * | 1983-12-30 | 1990-12-20 | Boeing Co | AGING AT RELATIVELY LOW TEMPERATURES OF LITHIUM-CONTAINING ALUMINUM ALLOYS. |
| US4648913A (en) * | 1984-03-29 | 1987-03-10 | Aluminum Company Of America | Aluminum-lithium alloys and method |
| DE3613224A1 (en) * | 1985-08-20 | 1987-02-26 | Boeing Co | ALUMINUM LITHIUM ALLOY |
-
1986
- 1986-11-26 CA CA000523887A patent/CA1291927C/en not_active Expired - Fee Related
- 1986-11-26 ES ES86420293T patent/ES2014248B3/en not_active Expired - Lifetime
- 1986-11-26 IL IL80765A patent/IL80765A0/en unknown
- 1986-11-26 AT AT86420293T patent/ATE52109T1/en not_active IP Right Cessation
- 1986-11-26 EP EP86420293A patent/EP0227563B1/en not_active Expired - Lifetime
- 1986-11-26 DE DE8686420293T patent/DE3670510D1/en not_active Revoked
- 1986-11-27 JP JP61283024A patent/JPS62142752A/en active Pending
- 1986-11-27 BR BR8605809A patent/BR8605809A/en unknown
Also Published As
| Publication number | Publication date |
|---|---|
| ES2014248B3 (en) | 1990-07-01 |
| DE3670510D1 (en) | 1990-05-23 |
| EP0227563A1 (en) | 1987-07-01 |
| CA1291927C (en) | 1991-11-12 |
| EP0227563B1 (en) | 1990-04-18 |
| ATE52109T1 (en) | 1990-05-15 |
| BR8605809A (en) | 1987-08-25 |
| IL80765A0 (en) | 1987-02-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8317947B2 (en) | Aluminum alloy sheet for press forming | |
| Vercammen et al. | Cold rolling behaviour of an austenitic Fe–30Mn–3Al–3Si TWIP-steel: the importance of deformation twinning | |
| Fan et al. | Investigation on strengthening of 6A02 aluminum alloy sheet in hot forming-quenching integrated process with warm forming-dies | |
| Furukawa et al. | Factors influencing the flow and hardness of materials with ultrafine grain sizes | |
| CN105671358B (en) | Copper alloy plate, copper alloy part and connector | |
| Stubbington et al. | Improvements in the fatigue strength of Ti-6Al-4V through microstructure control | |
| JPS62142752A (en) | Heat treatment of lithium-containing aluminum alloy | |
| EP2212444B2 (en) | Recrystallized aluminum alloys with brass texture and methods of making the same | |
| WO2013007471A1 (en) | Method of manufacturing an al-mg alloy sheet product | |
| EP2706125A1 (en) | Copper alloy sheet material and process for producing same | |
| Li et al. | Mechanical behavior of ultrafine-grained Ti-6Al-4V alloy produced by severe warm rolling: the influence of starting microstructure and reduction ratio | |
| Cho et al. | Microstructure and mechanical properties of Al-Si-Mg alloys fabricated by twin roll casting and subsequent symmetric and asymmetric rolling | |
| Kusakin et al. | Advanced thermomechanical processing for a high-Mn austenitic steel | |
| GB1603690A (en) | Process for the treatment of sheets of aluminium alloys | |
| JPS6324048A (en) | Production of zircaloy 2 or zircaloy 4 strip in partially recrystallized state and strip produced | |
| US4812178A (en) | Method of heat treatment of Al-based alloys containing Li and the product obtained by the method | |
| Hu et al. | Relationship between precipitation behavior and loading orientations of the creep-aged Al–Cu–Li single crystal | |
| Lee et al. | The effect of off-axis thermomechanical processing on the mechanical behavior of textured 2095 Al–Li alloy | |
| Zhang et al. | Hot-compression behavior of Al-1Mn-1Mg alloy | |
| CN114525433B (en) | Finished product annealing treatment method of aluminum alloy plate strip for new energy battery | |
| CN109666879B (en) | ZK61M magnesium alloy for aerospace | |
| CA3062762A1 (en) | Titanium alloy-based sheet material for low- temperature superplastic deformation | |
| Yang et al. | Anisotropy evolution of wide magnesium alloy foils during continuous electroplastic rolling | |
| Edmunds | Season Cracking of brass | |
| Zhang et al. | Effect of pre-annealing treatment on the microstructure and mechanical properties of extruded Al–Zn–Mg–Cu alloy bars |