CN1274392A - 特别适用于航空应用的、新的可焊、耐腐蚀、高镁含量的铝－镁合金 - Google Patents

特别适用于航空应用的、新的可焊、耐腐蚀、高镁含量的铝－镁合金 Download PDF

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Publication number
CN1274392A
CN1274392A CN99801242A CN99801242A CN1274392A CN 1274392 A CN1274392 A CN 1274392A CN 99801242 A CN99801242 A CN 99801242A CN 99801242 A CN99801242 A CN 99801242A CN 1274392 A CN1274392 A CN 1274392A
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aluminium
weight
magnesium
magnesium alloy
scandium
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CN1103827C (zh
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B·兰克佐斯基
V·叶拉金
R·劳
V·萨克哈罗夫
Y·费拉托夫
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Airbus Operations GmbH
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Daimler Benz AG
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Preventing Corrosion Or Incrustation Of Metals (AREA)
  • Powder Metallurgy (AREA)
  • Arc Welding In General (AREA)
  • Laminated Bodies (AREA)
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Abstract

可焊、高镁含量的铝—镁合金,由至少5—6重量%镁(Mg)、0.05—1.5重量%锆(Zr)、0.05—0.12重量%锰(Mn)、0.01—0.2重量%钛(Ti)、0.05—0.5重量%一种或多种钪族元素和/或铽(Tb),其中至少含有钪、0.1—0.2重量%铜(Cu)和/或0.1—0.4重量%锌(Zn)以及铝(Al)和不可避免的杂质,杂质中至多有0.1重量%硅(Si)。

Description

特别适用于航空应用的、新的 可焊、耐腐蚀、高镁含量的铝-镁合金
本发明涉及一种可焊、耐腐蚀、高镁含量的铝-镁合金，它含有一种三元铝-钪-锆相作为基本成分。这种合金已于例如US 5,624,632中已知，且由于它的低密度、高强度和耐腐蚀而首先用于航空应用中。加入稀土或类似稀土元素能在该铝-镁合金中产生弥散体，按上述US专利，这种弥散体产生较高的强度和耐腐蚀性。上述US专利来叙及这种合金的可焊接性。
本发明的目的是提供一种可焊、耐腐蚀、高镁含量的铝-镁合金，其强度和耐腐蚀性至少与所说已知合金一样好，并显示了一种高的再结晶临界值，这导致好的可焊接性。该目的可按权利要求1的铝-镁合金达到。
与所说已知合金相比，该合金首先显示了特别低的锰含量，但令人惊异地具备了改进的耐腐蚀性，主要是由这种合金制成的部件的激敏状态下、例如当冷成型的部件在一段长时间内经受升高的温度。假设该有利性质主要由锰对钪的比例来决定。在锰对钪之比＜2时已观察到了改进的耐腐蚀性。具有抑制粒子生长作用的钛的含量未包含在已知合金中有助于增加强度，因为钛可替代三元Al-Sc-Zr相中的锆，然后钛在其中的可溶性低于锆的可溶性。
加入Cu和/或Zn增加了强度，这可回溯到Al-Cu或Al-Zn相的已知的高强度。选择有关的浓度上限，以防止Cu减小可焊性，且防止Zn减小耐腐蚀性。
现已证明，至少在某种限度内钪可被铽或被铈替代。但是必须加入比被替代的钪量更多的铽，以获得不变的性能。
一种适用于航空应用的、特别适宜的合金含有至少0.15重量％钪。优选加入0.05％-0.35重量％的镧系元素(Lanthaniden)，该含量范围是针对使用一种镧系混合物时的混合物总重量而言的。该合金承受至多0.1重量％的硅杂质；初步地说，高于这个含量水平则损伤合金的动力性能。

Claims (5)

1.可焊、耐腐蚀、高镁含量的铝-镁合金，由至少5-6重量％镁(Mg)、0.05-0.15重量％锆(Zr)、0.05-0.12重量％锰(Mn)、0.01-0.2重量％钛(Ti)、0.05-0.5重量％一种或多种钪族元素和/或铽(Tb)，其中至少含有钪、0.1-0.2重量％铜(Cu)和/或0.1-0.4重量％锌(Zn)以及铝(Al)和不可避免的杂质，杂质中至多有0.1重量％硅(Si)。
2.按权利要求1的铝-镁合金，其特征在于，锰与钪的含量比小于2。
3.按权利要求1或2的铝-镁合金，其特征在于，含有至少0.15重量％钪(Sc)。
4.按权利要求1至3之一的铝-镁合金，其特征在于，含有0.05-0.35重量％的一种或多种镧系元素、尤其是铈(Ce)、钕(Nd)、铕(Eu)、钆(Gd)、镝(Dy)、钬(Ho)或铒(Er)。
5.用于飞机、特别是用于机身制造的、焊接的构件，由按权利要求1-4中之一的铝-镁合金组成。
CN99801242A 1998-08-21 1999-08-10 特别适用于航空应用的、新的可焊、耐腐蚀、高镁含量的铝－镁合金 Expired - Fee Related CN1103827C (zh)

Applications Claiming Priority (2)

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DE19838018.6 1998-08-21
DE19838018A DE19838018C2 (de) 1998-08-21 1998-08-21 Geschweißtes Bauteil aus einer schweißbaren, korrosionsbeständigen hochmagnesiumhaltigen Aluminium-Magnesium-Legierung

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CN1103827C CN1103827C (zh) 2003-03-26

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US (1) US6531004B1 (zh)
EP (1) EP1029097B1 (zh)
JP (1) JP2002523622A (zh)
CN (1) CN1103827C (zh)
CA (1) CA2306912C (zh)
DE (2) DE19838018C2 (zh)
ES (1) ES2242427T3 (zh)
RU (1) RU2226565C2 (zh)
WO (1) WO2000011232A1 (zh)

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CN101863307A (zh) * 2009-04-15 2010-10-20 阿勒里斯铝业科布伦茨有限公司 用于飞机机身的蒙皮板
CN104195387A (zh) * 2014-09-05 2014-12-10 天津立中合金集团有限公司 一种轮胎模具用高纯净铝镁合金材料及其制备方法
CN104498785A (zh) * 2014-11-23 2015-04-08 北京工业大学 一种Al-Mg-Er-Zr耐热铝合金及其制备工艺
CN101863307B (zh) * 2009-04-15 2016-12-14 阿勒里斯铝业科布伦茨有限公司 用于飞机机身的蒙皮板
CN107460380A (zh) * 2017-09-04 2017-12-12 佛山科学技术学院 一种高强耐蚀铝合金及其制备方法

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CN101863307A (zh) * 2009-04-15 2010-10-20 阿勒里斯铝业科布伦茨有限公司 用于飞机机身的蒙皮板
CN101863307B (zh) * 2009-04-15 2016-12-14 阿勒里斯铝业科布伦茨有限公司 用于飞机机身的蒙皮板
CN104195387A (zh) * 2014-09-05 2014-12-10 天津立中合金集团有限公司 一种轮胎模具用高纯净铝镁合金材料及其制备方法
CN104195387B (zh) * 2014-09-05 2016-03-16 天津立中合金集团有限公司 一种轮胎模具用高纯净铝镁合金材料及其制备方法
CN104498785A (zh) * 2014-11-23 2015-04-08 北京工业大学 一种Al-Mg-Er-Zr耐热铝合金及其制备工艺
CN104498785B (zh) * 2014-11-23 2016-07-06 北京工业大学 一种Al-Mg-Er-Zr耐热铝合金及其制备工艺
CN107460380A (zh) * 2017-09-04 2017-12-12 佛山科学技术学院 一种高强耐蚀铝合金及其制备方法
CN107460380B (zh) * 2017-09-04 2019-07-09 佛山科学技术学院 一种高强耐蚀铝合金及其制备方法

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DE59912240D1 (de) 2005-08-11
EP1029097B1 (de) 2005-07-06
WO2000011232A1 (de) 2000-03-02
RU2226565C2 (ru) 2004-04-10
EP1029097A1 (de) 2000-08-23
CN1103827C (zh) 2003-03-26
DE19838018C2 (de) 2002-07-25
US6531004B1 (en) 2003-03-11
ES2242427T3 (es) 2005-11-01
DE19838018A1 (de) 2000-03-02
JP2002523622A (ja) 2002-07-30
CA2306912C (en) 2008-12-23
CA2306912A1 (en) 2000-03-02

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