Aluminum alloy sheet for lithographic printing plate
    43.
    发明申请
    Aluminum alloy sheet for lithographic printing plate 有权
    平版印刷版铝合金板

    公开(公告)号:US20110104001A1

    公开(公告)日:2011-05-05

    申请号:US12590032

    申请日:2009-10-30

    摘要: An aluminum alloy sheet for a lithographic printing plate includes 0.03 to 0.15% (mass %, hereinafter the same) of Si, 0.2 to 0.7% of Fe, 0.05 to 0.5% of Mg, 0.003 to 0.05% of 11, and 30 to 300 ppm of Ga, with the balance being aluminum and inevitable impurities, a surface area of the aluminum alloy sheet having an average recrystallized grain size of 50 μm or less in a direction perpendicular to a rolling direction, an Mg concentration that is higher than the average Mg concentration by a factor of 5 to 50, and a Ga concentration that is higher than the average Ga concentration by a factor of 2 to 20, the surface area being an area up to a depth of 0.2 μm from the surface of the aluminum alloy sheet.

    摘要翻译: 用于平版印刷版的铝合金板包括Si:0.03〜0.15%(质量%,以下相同)Si:0.2〜0.7%的Fe,0.05〜0.5%的Mg,0.003〜0.05%的11,30〜300 ppm的Ga,余量为铝和不可避免的杂质,在与轧制方向垂直的方向上的平均再结晶粒径为50μm以下的铝合金板的表面积,高于平均值的Mg浓度 Mg浓度为5〜50倍,Ga浓度高于平均Ga浓度2〜20倍,表面积为距铝合金表面0.2μm以上的面积 片。

    Method Of Making A Structural Element For Aeronautical Construction Comprising Differential Work-Hardening
    46.
    发明申请
    Method Of Making A Structural Element For Aeronautical Construction Comprising Differential Work-Hardening 审中-公开
    制造包含差分工作硬化的航空结构的结构要素的方法

    公开(公告)号:US20070246137A1

    公开(公告)日:2007-10-25

    申请号:US11734843

    申请日:2007-04-13

    IPC分类号: C22C21/12 C22F1/04

    摘要: A process for fabricating a worked product or a monolithic multi-functional structural element comprising aluminium alloy includes a hot working step and at least one transformation step by cold plastic deformation after the hot transformation step. At least two zones of the structural element have imposed generalized average plastic deformations and the imposed deformations are different by at least 2%. Structural elements can be fabricated, particularly for aeronautical construction, with properties that are variable while their geometric characteristics are identical to those of existing components. The process is economic and controllable, and properties can be varied for parts not requiring any artificial ageing.

    摘要翻译: 制造加工产品的方法或包括铝合金的整体式多功能结构元件包括热加工步骤和热变形步骤之后的冷塑性变形的至少一个转变步骤。 结构元件的至少两个区域已经施加了广义平均塑性变形,并且所施加的变形至少不同于2%。 可以制造结构元件,特别是用于航空结构,具有可变的性质,而其几何特征与现有部件的几何特征相同。 该过程是经济可控的,并且对于不需要任何人造时效的部件,性能可以变化。

    High strength aluminum alloy
    49.
    发明授权

    公开(公告)号:US07125459B2

    公开(公告)日:2006-10-24

    申请号:US11018262

    申请日:2004-12-21

    申请人: Alex Cho

    发明人: Alex Cho

    IPC分类号: C22F1/057

    CPC分类号: C22C21/12 C22F1/057

    摘要: A process for thermally treating an article made from an alloy comprising at least aluminum and copper. The process comprises solid solution heat treating the article, quenching the article, heating the article to a first temperature of from about 275 to about 340° F. and artificially aging. The article is artificially aged at the first temperature for a duration of at least 30 minutes. The article is artificially aged at a second temperature of from about 325 to about 380° F. for a duration of from about 4 hours to about 36 hours. The second temperature is greater than the first temperature by at least 10° F.