JPS6318034A - Aluminum-base powder metallurgical alloy combining high strength with stress corrosion cracking resistance - Google Patents
Aluminum-base powder metallurgical alloy combining high strength with stress corrosion cracking resistanceInfo
- Publication number
- JPS6318034A JPS6318034A JP61160773A JP16077386A JPS6318034A JP S6318034 A JPS6318034 A JP S6318034A JP 61160773 A JP61160773 A JP 61160773A JP 16077386 A JP16077386 A JP 16077386A JP S6318034 A JPS6318034 A JP S6318034A
- Authority
- JP
- Japan
- Prior art keywords
- alloy
- grain size
- aluminum
- stress corrosion
- corrosion cracking
- 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.)
- Granted
Links
- 239000000956 alloy Substances 0.000 title claims abstract description 38
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 27
- 230000007797 corrosion Effects 0.000 title claims abstract description 21
- 238000005260 corrosion Methods 0.000 title claims abstract description 21
- 238000005336 cracking Methods 0.000 title claims abstract description 19
- 239000000843 powder Substances 0.000 title claims abstract description 10
- 229910000765 intermetallic Inorganic materials 0.000 claims abstract description 12
- 239000012535 impurity Substances 0.000 claims abstract description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 14
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 13
- 239000013078 crystal Substances 0.000 claims description 11
- 239000000203 mixture Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 abstract description 23
- 229910000838 Al alloy Inorganic materials 0.000 abstract description 12
- 238000001816 cooling Methods 0.000 abstract description 7
- 238000000034 method Methods 0.000 abstract description 6
- 229910052726 zirconium Inorganic materials 0.000 abstract description 4
- 229910052804 chromium Inorganic materials 0.000 abstract description 3
- 229910052802 copper Inorganic materials 0.000 abstract description 3
- 229910052749 magnesium Inorganic materials 0.000 abstract description 3
- 229910052748 manganese Inorganic materials 0.000 abstract description 3
- 229910052725 zinc Inorganic materials 0.000 abstract description 3
- 238000009689 gas atomisation Methods 0.000 abstract description 2
- 229910052742 iron Inorganic materials 0.000 abstract description 2
- 229910052750 molybdenum Inorganic materials 0.000 abstract description 2
- 229910052759 nickel Inorganic materials 0.000 abstract description 2
- 229910052721 tungsten Inorganic materials 0.000 abstract description 2
- 229910052720 vanadium Inorganic materials 0.000 abstract description 2
- 230000001105 regulatory effect Effects 0.000 abstract 1
- 230000035882 stress Effects 0.000 description 18
- 238000011282 treatment Methods 0.000 description 11
- 230000032683 aging Effects 0.000 description 9
- 239000000243 solution Substances 0.000 description 9
- 230000000694 effects Effects 0.000 description 7
- 238000001125 extrusion Methods 0.000 description 5
- 238000010438 heat treatment Methods 0.000 description 5
- 239000002245 particle Substances 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- 238000004663 powder metallurgy Methods 0.000 description 4
- 238000002360 preparation method Methods 0.000 description 4
- 238000012545 processing Methods 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 150000001875 compounds Chemical class 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 229910019086 Mg-Cu Inorganic materials 0.000 description 2
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 2
- 230000000052 comparative effect Effects 0.000 description 2
- 238000007796 conventional method Methods 0.000 description 2
- 239000006185 dispersion Substances 0.000 description 2
- 238000001035 drying Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 230000001376 precipitating effect Effects 0.000 description 2
- 238000001953 recrystallisation Methods 0.000 description 2
- 239000006104 solid solution Substances 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 229910018182 Al—Cu Inorganic materials 0.000 description 1
- 235000002597 Solanum melongena Nutrition 0.000 description 1
- 244000061458 Solanum melongena Species 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 238000007872 degassing Methods 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000003292 diminished effect Effects 0.000 description 1
- 238000004299 exfoliation Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 238000004881 precipitation hardening Methods 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 238000007712 rapid solidification Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000011780 sodium chloride Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000009849 vacuum degassing Methods 0.000 description 1
Abstract
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明は粉末冶金法によるアルミニウム基合金材に関し
、さらに詳しくは、本発明は引張強さおよび耐応力腐食
割れ性にすぐれたアルミニウム基粉末冶金合金材料に関
する。Detailed Description of the Invention (Industrial Application Field) The present invention relates to an aluminum-based alloy material produced by powder metallurgy, and more specifically, the present invention relates to an aluminum-based powder metallurgy material having excellent tensile strength and stress corrosion cracking resistance. Regarding alloy materials.
（従来の技術）
従来高強度アルミニウム合金としてはＡｌ−Ｃｕ −Ｍ
ｇ系（２０００系）およびＡ ｌ −Ｚ ｎ −Ｍｇ
−Ｃｕ系（７０００系）合金が良く知られている。これ
ら合金に含まれるＣｕ、Ｍｇ、ＺｎはＡＪＩに対して高
温で固溶度か比較的大きく、低温で小さいため析出硬化
元素として有効であることが知られており、各種の熱処
理により望みの機械的性質を有する材料を得ている。ま
たアルミニウム合金の強度を高めるもう１つの方法とし
て高温て固溶度が小さく、かつ拡散しにくい化合物を形
成する元素（Ｚｒ、Ｃｒ、Ｍｎなど）を添加し、それら
の化合物による分散強化あるいは再結晶粒の粗大化防止
をはかる方法がある。(Prior art) As a conventional high-strength aluminum alloy, Al-Cu -M
g series (2000 series) and A l -Z n -Mg
-Cu-based (7000-based) alloys are well known. Cu, Mg, and Zn contained in these alloys are known to be effective as precipitation hardening elements because their solid solubility relative to AJI is relatively large at high temperatures and small at low temperatures. We have obtained a material with specific properties. Another method to increase the strength of aluminum alloys is to add elements (Zr, Cr, Mn, etc.) that form compounds that have low solid solubility and are difficult to diffuse at high temperatures, and to strengthen the aluminum alloy by dispersion strengthening or recrystallization. There are ways to prevent grains from becoming coarse.
一方、航空、宇宙分野の機器に用いられる構造材におい
ては単に高強度であるばかりでなく、腐食性環境下で応
力を受けた時に割れにくい特性が重要な材料特性として
要求される。On the other hand, important material properties for structural materials used in equipment in the aviation and space fields are not only high strength but also resistance to cracking when subjected to stress in corrosive environments.
従って、以上述べたような２つの特性、すなわち高強度
で耐応力腐食割れ性に優れる材料として、これまてはＡ
Ｍ−Ｚｎ−Ｍｇ−Ｃｕ系の７０７５．７４７５．７０５
０．７１５０合金が使用されてきた。Therefore, as a material with the above two characteristics, namely high strength and excellent stress corrosion cracking resistance, A
M-Zn-Mg-Cu series 7075.7475.705
0.7150 alloy has been used.
ところてこのようなアルミニウム合金の製造は従来性わ
れているアルミニウム合金の溶湯から鋳塊を作り、これ
を加工して素材とする方法を用いるか、このような方法
ては、鋳塊の凝固時の冷却速度か小さいため比較的大き
な結晶粒および金属間化合物が形成され、その後の加工
、熱処理工程まてその影響か残るため最終的に得られる
材料の特性向上は限界がある。例えば７０００系合金は
最高強度か得られる熱処理条件では剥離腐食あるいは応
力腐食割れか発生しやすいため、強度をある程度犠牲に
して過時効処理を施した材料とする必要かあった。However, in order to manufacture such aluminum alloys, the conventional method is to create an ingot from molten aluminum alloy and process this into a raw material. Because the cooling rate is slow, relatively large crystal grains and intermetallic compounds are formed, and their effects remain in subsequent processing and heat treatment steps, so there is a limit to the improvement in the properties of the final material. For example, 7000 series alloys are prone to exfoliation corrosion or stress corrosion cracking under heat treatment conditions that provide the highest strength, so it was necessary to sacrifice some strength and use an over-aged material.
一方、強度および耐応力腐食割れ性を向上させるため、
Ａ文−Ｚ ｎ −Ｍ ｇ −Ｃｕ合金の溶湯をアトマイ
ズし、熱間加工、溶体化、急冷および二段の人工時効処
理する方法か提案されている。（米国特許第３，５６３
，８１４号）。On the other hand, to improve strength and stress corrosion cracking resistance,
A method has been proposed in which a molten metal of A-Zn-Mg-Cu alloy is atomized, followed by hot working, solution treatment, rapid cooling, and two-stage artificial aging treatment. (U.S. Patent No. 3,563
, No. 814).
（発明か解決しようとする問題点）
しかしなから近年、構造部材の軽量化に伴い材料特性の
より一層の向上が望まれ、従来品以上の強度及び耐応力
腐食割れ性を有する素材か要求されている。(Problem to be solved by the invention) However, in recent years, as structural members have become lighter, there has been a desire for further improvements in material properties, and materials with greater strength and stress corrosion cracking resistance than conventional products are required. ing.
したかって本発明は強度および耐応力腐食割れ性が優れ
た組成の新規な高強度耐応力腐食割れ性アルミニウム基
粉末冶金合金材を提供することを目的とする。Therefore, an object of the present invention is to provide a novel high-strength, stress corrosion cracking resistant aluminum-based powder metallurgical alloy material having a composition excellent in strength and stress corrosion cracking resistance.
（問題点を解決するための手段）
本発明者らは従来のアルミニウム合金材の欠点を克服す
べく鋭意研究を重ねた結果、Ａ、Ｑ−Ｚｎ−ｐＪｉ ｇ
−Ｃｕ系粉末冶金合金材においてＺｒを０．３〜１％
添加し、平均結晶粒径を３０＃Ｌｍ以下、金属間化合物
粒径な５μｍ以下にそれでれ規制することにより強度お
よび耐応力腐食割れ性を向上しうることを見出し、この
知見に基づき本発明をなすにいたった。(Means for Solving the Problems) As a result of intensive research by the present inventors to overcome the drawbacks of conventional aluminum alloy materials, A, Q-Zn-pJig
-0.3 to 1% Zr in Cu-based powder metallurgy alloy material
It was discovered that the strength and stress corrosion cracking resistance could be improved by controlling the average crystal grain size to 30 #Lm or less and the intermetallic compound grain size to 5 μm or less, and based on this knowledge, the present invention was developed. It turned out to be eggplant.
すなわち、本発明はＺｎ５〜ｌＯ％、Ｍｇ２〜５％、Ｃ
ｕＯ，５〜３％、ＺｒＯ，３〜１％（以上重量％、以下
同様）を含有し、残部かＡｎと不可避不純物からなる合
金組成を有し、かつ３０Ｂｍ以下のモ均結晶粒径および
５ｇｍ以下の金属間化合物粒径な有することを特徴とす
るアルミニウム基粉末冶金合金材料を提供するものであ
る。That is, in the present invention, Zn5-10%, Mg2-5%, C
It has an alloy composition containing uO, 5 to 3%, ZrO, 3 to 1% (the above weight %, the same applies hereinafter), the balance consisting of An and unavoidable impurities, and has a uniform crystal grain size of 30 Bm or less and 5 gm The present invention provides an aluminum-based powder metallurgical alloy material characterized by having the following intermetallic compound particle size.
本発明においてアルミニウム合金材料中の各成分組成を
限定した意義は次の通りである。The significance of limiting the composition of each component in the aluminum alloy material in the present invention is as follows.
Ｚｎは５〜ｌＯ％とする。合金組成中のＺｎはアルミニ
ウム中に固溶または時効析出することにより合金の強度
を高めるか、５％未満ではその効果が少なく、１０％を
越えると金属間化合物が粗大となり材料の延性か低下す
る。Zn is 5 to 10%. Zn in the alloy composition improves the strength of the alloy by forming a solid solution in aluminum or precipitating during aging. If it is less than 5%, the effect is small, and if it exceeds 10%, the intermetallic compounds become coarse and the ductility of the material decreases. .
Ｍｇは２〜５％とする。Ｍｇもアルミニウム中に固溶ま
たは時効析出することにより合金の強度を向上させるか
、２％未満ではその効果か少なく、５％を越えると金属
間化合物か粗大となり材料の延性か低Ｆする。Mg should be 2 to 5%. Mg also improves the strength of the alloy by being dissolved in aluminum or precipitated during aging, but if it is less than 2%, the effect is small, and if it exceeds 5%, intermetallic compounds become coarse and the ductility of the material decreases.
Ｃｕは０．５〜３％とする。Ｃｕもアルミニウム中に固
溶または時効析出することにより合金の強度を向１−さ
せるか、０．５％未満てはその効果か少なく、３％を越
えると材料の耐食性か低下する。Cu is set to 0.5 to 3%. Cu also improves the strength of the alloy by forming a solid solution in aluminum or precipitating during aging. If it is less than 0.5%, the effect is small, and if it exceeds 3%, the corrosion resistance of the material is reduced.
Ｚｒは０．３〜１％とする。Ｚｒはアルミニウム中ての
固溶度か小さく、化合物として析出するので、これを微
細均一に分散させることによる分散強化効果として、強
度か向上し、さらには再結晶による結晶粒粗大化防止効
果として耐応力腐食割れ性改善か得られる。０．３％以
下ではこれらの効果か少なく１％以上では初晶として粗
大結晶か晶出するため材料の延性が低下する。Zr is set to 0.3 to 1%. Zr has a low solid solubility in aluminum and precipitates as a compound, so dispersing it finely and uniformly improves strength as a dispersion strengthening effect, and further improves resistance by preventing crystal grain coarsening due to recrystallization. Stress corrosion cracking resistance can be improved. If it is less than 0.3%, these effects will be diminished, and if it is more than 1%, coarse crystals will crystallize as primary crystals, resulting in a decrease in the ductility of the material.
なお、本発明のアルミニウム基合金材料にＭｎ、Ｃｒ、
Ｃｏ、Ｆｅ、Ｎｉ、Ｖ、Ｍｏ、Ｗなどを添加する必要は
ないか１種または２種以上少量（０，５％以下）添加し
ても何ら特性を損ねるものではない。Note that the aluminum-based alloy material of the present invention contains Mn, Cr,
There is no need to add Co, Fe, Ni, V, Mo, W, etc., or even if one or more of them are added in small amounts (0.5% or less), the properties will not be impaired in any way.
次に、本発明のアルミニウム基合金材料において平均結
晶粒径を３０μｍ以下、金属間化合物径を５＃Ｌｍ以下
とする。平均結晶粒径か３０μｍを越えると耐応力腐食
割れ性の改善か十分でなく、金属間化合物粒径か５ｇｍ
を越えると延性か劣化する。Next, in the aluminum-based alloy material of the present invention, the average crystal grain size is set to 30 μm or less, and the intermetallic compound diameter is set to 5 #Lm or less. If the average crystal grain size exceeds 30 μm, the improvement in stress corrosion cracking resistance is insufficient, and the intermetallic compound grain size exceeds 5 gm.
Exceeding this will result in deterioration of ductility.
本発明のアルミニウム基合金材料の製造の際、目標の平
均結晶粒径および金属間化合物径を有する粉末合金はア
ルミニウム合金の溶湯な、好ましくは冷却速度５００℃
／ ｓ ｅ ｃ以上においてガスアトマイズ法その他の
方法により処理し急冷凝固させることにより製造するこ
とができる。In producing the aluminum-based alloy material of the present invention, the powder alloy having the target average grain size and intermetallic compound size is a molten aluminum alloy, preferably at a cooling rate of 50°C.
/ sec or more by a gas atomization method or other method, followed by rapid solidification.
本発明においてアトマイズ法により処理して得られるア
ルミニウム合金粉末の粒径は １５０終ｍ以下である。In the present invention, the particle size of the aluminum alloy powder obtained by processing by the atomization method is 150 mm or less.
通常、この粉末を真密度の７０〜９０％の密度になるよ
う予備成形し、３００〜４５０℃で真空脱ガスを行った
後、同温度で真密度になるよう圧縮成形しビレットとす
る。さらにこのビレットに熱間加工（押出、鍛造または
圧延）を施し目的の素材とする。そしてさらに常法によ
る溶体化、急冷、時効の熱処理を順次行い、所望の材料
特性を有する素材とする。Usually, this powder is preformed to a density of 70 to 90% of the true density, vacuum degassed at 300 to 450°C, and then compression molded to the true density at the same temperature to form a billet. Further, this billet is subjected to hot processing (extrusion, forging, or rolling) to obtain the desired material. Then, heat treatments such as solution treatment, quenching, and aging are sequentially performed using conventional methods to obtain a material having desired material properties.
（実施例） 次に実施例により本発明の詳細な説明する。(Example) Next, the present invention will be explained in detail with reference to Examples.
実施例１〜８
第１表に示す合金Ｎｏ、１〜８の組成の合金を下記に示
す工程により加工して棒状素材を作製し、それぞれ実施
例の試料１〜８とした。Examples 1 to 8 Bar-shaped materials were produced by processing alloys having the compositions of Alloy Nos. 1 to 8 shown in Table 1 through the steps shown below, and were designated as Samples 1 to 8 of Examples, respectively.
（試料作製工程） ｌ）合金調製、溶解 ２）アルゴンガス下アトマイズ 冷却速度１０００’ｃ／ｓｅｃ以上 粉末の平均粒径１００終ｍ ３）予＠成形 真密度の８０％ ４）脱ガス ４００℃で真空脱ガス ５）熱間プレス ４００℃で真密度まで圧縮成形してビレットとする。(Sample preparation process) l) Alloy preparation and melting 2) Atomization under argon gas Cooling rate 1000'c/sec or more Powder average particle size 100m 3) Pre-forming 80% of true density 4) Degassing Vacuum degassing at 400℃ 5) Hot press Compression molding is performed at 400°C to true density to form a billet.
６）押出 ４００℃、押出比１４で直径３０ｍｍの棒材とする。6) Extrusion A bar with a diameter of 30 mm is prepared at 400° C. and at an extrusion ratio of 14.
７）熱処理 ４８８℃で１時間溶体化処理後水冷する。7) Heat treatment After solution treatment at 488° C. for 1 hour, it is cooled with water.
次いで１２０℃で２４時間さらに１６３℃で２４時間時
効処理する。Then, aging treatment is performed at 120°C for 24 hours and further at 163°C for 24 hours.
得られた各試料について結晶粒径（ＳＴ面で測定）、化
合物粒径の測定および引張試験、耐応力腐食割れ試験を
行った。その結果を第２表に示す。Each of the obtained samples was subjected to measurements of crystal grain size (measured on the ST plane), compound particle size, tensile test, and stress corrosion cracking resistance test. The results are shown in Table 2.
（耐応力腐食割れ性試験方法） 試験条件 ＡＳＴＭ Ｇ４７による。(Stress corrosion cracking resistance test method) Test conditions: Based on ASTM G47.
（１）応力負荷：押出丸棒の円周方向。(1) Stress load: circumferential direction of extruded round bar.
（２）サイクルＨＮａＣ文溶液溶液０分間浸漬、５０分
間乾燥。(2) Cycle immersion in HNaC solution for 0 minutes and drying for 50 minutes.
（３）Ｎ ａ Ｃｌ溶液：濃度３．５％、ＰＨ６，４〜
７．２、温度２５±３°Ｃ１試
料表面／ｄゴあた９３．２文
以上の量使用、溶液は１週間
毎に更新。(3) NaCl solution: concentration 3.5%, PH6.4~
7.2, Temperature: 25±3°C 1 Sample surface/d go at 93.2 min or more, solution updated every week.
（４）乾 燥：温度２７±１’Ｃ１温度４５±６％（
５）試験期間：２０日間
比較例
第１表に示すＮｏ、９．１０．１１．１２の組成の合金
を用いて下記に示す工程により棒状素材を調製し、それ
ぞれ比較例としての試料９．１ｏ、１１．１２とし、こ
れらの試料について実施例の場合と同様の測定および試
験を行った。その結果も第２表に示す。(4) Drying: Temperature 27±1'C1 Temperature 45±6% (
5) Test period: 20 days Comparative example Rod-shaped materials were prepared using the alloys No. 9, 9, 10, 11 and 12 shown in Table 1 according to the steps shown below, and Sample 9.1o was used as a comparative example. , 11.12, and the same measurements and tests as in the examples were performed on these samples. The results are also shown in Table 2.
（試料作製工程） ｌ）合金調製、溶解、鋳造 直径８０ｍｍのビレットとする。(Sample preparation process) l) Alloy preparation, melting, casting A billet with a diameter of 80 mm is made.
２）均質化処理 ビレットを４７０℃で２４時間均質化処理する。2) Homogenization treatment The billet is homogenized at 470° C. for 24 hours.
３）押出 ４００℃、押出比１４、直径３０ｍｍの棒材とする。3) Extrusion The temperature is 400°C, the extrusion ratio is 14, and the bar is 30 mm in diameter.
４）熱処理
合金Ｎｏ、９；４６６°ＣＸ１．５時間溶体化処理後水
冷する。次いで、１０７℃×７時間と１７７°Ｃｘ７時
間の時効処理を行う。4) Heat treatment alloy No. 9: Solution treatment at 466° C. for 1.5 hours and then water cooling. Next, aging treatments are performed at 107°C for 7 hours and at 177°C for 7 hours.
合金Ｎｏ、ｌＯ；４７７°ＣＸ１．５時間溶体化処理後
水冷する。次いで、１２１″Ｃ×５時間と１６３℃×１
７時間の時効処理を行う。Alloy No., 1O: Solution treatment at 477° C. for 1.5 hours, followed by water cooling. Next, 121″C x 5 hours and 163°C x 1
Perform aging treatment for 7 hours.
合金Ｎｏ、１１．１２．４８８℃で１時間溶体化処理後
水冷する０次いで１２０℃で２４時間さらに１６３°Ｃ
で２４時間時効処理を行う。Alloy No. 11. 12. Solution treated at 488°C for 1 hour and then water cooled at 120°C for 24 hours and further at 163°C.
Aging treatment is performed for 24 hours.
これらの試料について実施例の場合と同様の試験を行っ
た。その結果を第２表に示した。The same tests as in the examples were conducted on these samples. The results are shown in Table 2.
これらの結果から明らかなように、試料１〜８は従来合
金試料９、ｌＯに比べ機械的性質が同等またはそれ以上
であり、かつ耐応力腐食割れ性が非常に改善されている
。As is clear from these results, Samples 1 to 8 have mechanical properties equivalent to or better than conventional alloy samples 9 and 1O, and have greatly improved stress corrosion cracking resistance.
また試料１１．１２は本発明の範囲内の成分の合金であ
るが、平均結晶粒径および金属間化合物粒径か大きいた
め機械的性質および耐応力腐食割（発明の効果）
本発明の高強度耐応力腐食割れ性アルミニウム基粉末冶
金合金材は強度および耐応力腐食割れ性の点ですぐれた
構造材を与える。したかって航空機材などに代表される
高度な材料特性が要求される部材用として特に好適であ
る。Samples 11 and 12 are alloys with components within the range of the present invention, but the average crystal grain size and intermetallic compound particle size are large, resulting in poor mechanical properties and stress corrosion resistance (effects of the invention).High strength of the present invention. Stress corrosion cracking resistant aluminum-based powder metallurgy alloy materials provide structural materials with excellent strength and stress corrosion cracking resistance. Therefore, it is particularly suitable for use in parts that require advanced material properties, such as aircraft materials.
Claims (1)
ｒ０．３〜１％（以上重量％）を含有し、残部がＡｌと
不可避不純物からなる合金組成を有し、かつ平均３０μ
ｍ以下の結晶粒径および５μｍ以下の金属間化合物粒径
を有することを特徴とする高強度耐応力腐食割れ性アル
ミニウム基粉末冶金合金。Zn5-10%, Mg2-5%, Cu0.5-3%, Z
It has an alloy composition containing 0.3 to 1% r (more than 1% by weight), the balance consisting of Al and unavoidable impurities, and has an average of 30μ
A high-strength, stress corrosion cracking-resistant aluminum-based powder metallurgical alloy characterized by having a crystal grain size of not more than 5 μm and an intermetallic compound grain size of not more than 5 μm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61160773A JPH0713275B2 (en) | 1986-07-10 | 1986-07-10 | High-strength stress corrosion cracking resistant aluminum-based powder metallurgy alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61160773A JPH0713275B2 (en) | 1986-07-10 | 1986-07-10 | High-strength stress corrosion cracking resistant aluminum-based powder metallurgy alloy |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS6318034A true JPS6318034A (en) | 1988-01-25 |
| JPH0713275B2 JPH0713275B2 (en) | 1995-02-15 |
Family
ID=15722140
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP61160773A Expired - Fee Related JPH0713275B2 (en) | 1986-07-10 | 1986-07-10 | High-strength stress corrosion cracking resistant aluminum-based powder metallurgy alloy |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0713275B2 (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH032345A (en) * | 1989-04-05 | 1991-01-08 | Pechiney Rech | Aluminum-base alloy of high young's modulus and mechanical strength and production of said alloy |
| US6585932B1 (en) * | 1999-05-24 | 2003-07-01 | Mantraco International, Inc. | Aluminum-based material and a method for manufacturing products from aluminum-based material |
| EP1726671A2 (en) * | 2005-05-26 | 2006-11-29 | Honeywell International, Inc. | High strength aluminium alloys for aircraft wheel and brake components |
| WO2008105303A1 (en) * | 2007-02-28 | 2008-09-04 | Kabushiki Kaisha Kobe Seiko Sho | High-strength and high-ductility al alloy and process for production of the same |
| JP2008240141A (en) * | 2007-02-28 | 2008-10-09 | Kobe Steel Ltd | HIGH STRENGTH AND HIGH DUCTILITY Al ALLOY, AND METHOD FOR PRODUCING THE SAME |
| JP2017109212A (en) * | 2015-12-15 | 2017-06-22 | 花王株式会社 | Method for laminating and shaping casting mold |
| JP2017186651A (en) * | 2016-02-11 | 2017-10-12 | エアバス・ディフェンス・アンド・スペース・ゲーエムベーハー | Al-Mg-Zn ALLOY WITH SCANDIUM FOR INTEGRAL CONSTRUCTION OF ALM STRUCTURES |
-
1986
- 1986-07-10 JP JP61160773A patent/JPH0713275B2/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH032345A (en) * | 1989-04-05 | 1991-01-08 | Pechiney Rech | Aluminum-base alloy of high young's modulus and mechanical strength and production of said alloy |
| US6585932B1 (en) * | 1999-05-24 | 2003-07-01 | Mantraco International, Inc. | Aluminum-based material and a method for manufacturing products from aluminum-based material |
| EP1726671A2 (en) * | 2005-05-26 | 2006-11-29 | Honeywell International, Inc. | High strength aluminium alloys for aircraft wheel and brake components |
| EP1726671A3 (en) * | 2005-05-26 | 2008-07-16 | Honeywell International, Inc. | High strength aluminium alloys for aircraft wheel and brake components |
| US7691214B2 (en) | 2005-05-26 | 2010-04-06 | Honeywell International, Inc. | High strength aluminum alloys for aircraft wheel and brake components |
| WO2008105303A1 (en) * | 2007-02-28 | 2008-09-04 | Kabushiki Kaisha Kobe Seiko Sho | High-strength and high-ductility al alloy and process for production of the same |
| JP2008240141A (en) * | 2007-02-28 | 2008-10-09 | Kobe Steel Ltd | HIGH STRENGTH AND HIGH DUCTILITY Al ALLOY, AND METHOD FOR PRODUCING THE SAME |
| GB2460780A (en) * | 2007-02-28 | 2009-12-16 | Kobe Steel Ltd | High strength and high-ductility Al alloy and process for production of the same |
| GB2460780B (en) * | 2007-02-28 | 2011-06-01 | Kobe Steel Ltd | High strength and high-ductility Al alloy and process for production of the same |
| US8444777B2 (en) | 2007-02-28 | 2013-05-21 | Kobe Steel, Ltd. | High-strength and high-ductility Al alloy and process for production of the same |
| JP2017109212A (en) * | 2015-12-15 | 2017-06-22 | 花王株式会社 | Method for laminating and shaping casting mold |
| JP2017186651A (en) * | 2016-02-11 | 2017-10-12 | エアバス・ディフェンス・アンド・スペース・ゲーエムベーハー | Al-Mg-Zn ALLOY WITH SCANDIUM FOR INTEGRAL CONSTRUCTION OF ALM STRUCTURES |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0713275B2 (en) | 1995-02-15 |
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