会员体验
专利管家(专利管理)
工作空间(专利管理)
风险监控(情报监控)
数据分析(专利分析)
侵权分析(诉讼无效)
联系我们
交流群
官方交流:
QQ群: 891211   
微信请扫码    >>>
现在联系顾问~
热词
    • 2. 发明申请
    • IMPROVEMENTS IN OR RELATING TO ALUMINIUM ALLOYS
    • 铝合金的改进或相关
    • WO1992018658A1
    • 1992-10-29
    • PCT/GB1992000658
    • 1992-04-10
    • ALCAN INTERNATIONAL LIMITEDGATENBY, Kevin, MichaelPALMER, Ian, Graham
    • ALCAN INTERNATIONAL LIMITED
    • C22F01/04
    • C22F1/04
    • This invention relates to aluminium alloys containing lithium which are particularly suitable for aerospace construction and have been found to have improved damage tolerance in regard to their fatigue crack deviation behaviour. The method of producing a damage tolerant sheet of lithium-containing aluminium alloy having reduced susceptibility to fatigue crack deviation comprising providing a sheet of the said alloy with an unaged structure, ageing the sheet at a temperature and for a time near to, at, or over the peak aged condition for that alloy based upon its proof stress properties sufficient to increase precipitation of at least one planar slip blocking phase, heating the sheet to an elevated temperature higher than its ageing temperature and holding the sheet at that temperature for a time sufficient to facilitate significant dissolution of the delta ' phase precipitates therein without significant dissolution of any planar slip blocking phase, and then cooling the sheet. Preferably the alloy has a composition within that specified for one of the registered alloys 8090, 8091, 2090 and 2091. The preferred post-ageing (reversion) conditions for 8090 are 4 minutes at 230 DEG C.
    • 本发明涉及特别适用于航空航天结构的含锂的铝合金,并且已经发现其具有关于它们的疲劳裂纹偏离行为的改进的损伤公差。 制造具有降低的疲劳裂纹偏差敏感性的含锂铝合金的耐损伤片材的方法,包括提供具有未老化结构的所述合金的片材,使片材在温度和时间附近, 超过该合金的峰值老化条件,其基于其足以增加至少一个平滑片粘结相的沉淀的证明应力特性,将片材加热到高于其老化温度的升高的温度,并将该片材在该温度下保持足够的时间 以促进三角洲相析出物在其中的显着溶解,而没有任何平面滑移阻挡相的显着溶解,然后冷却片材。 优选地,合金具有对于注册合金8090,8091,2090和2091中的一种的组成。对于8090,优选的后期老化(回复)条件在230℃下为4分钟。
    • 5. 发明申请
    • IMPROVEMENTS IN OR RELATING TO ALUMINIUM ALLOYS
    • 铝合金的改进或相关
    • WO1991008319A1
    • 1991-06-13
    • PCT/GB1990001851
    • 1990-11-28
    • ALCAN INTERNATIONAL LIMITEDGATENBY, Kevin, MichaelPALMER, Ian, GrahamGRIMES, Roger
    • ALCAN INTERNATIONAL LIMITED
    • C22F01/04
    • C22C21/00C22F1/04C22F1/057
    • This invention relates to aluminium alloys containing lithium which are particularly suitable for aerospace construction in that they possess improved cold rolling characteristics optionally with improved damage tolerence. A method of producing sheet or strip material is described which comprises the steps of: (a) providing, in a condition suitable for hot rolling, a billet of an alloy of the composition in weight percent: lithium 1.9 to 2.6; magnesium 0.4 to 1.4; copper 1.0 to 2,2; manganese 0 to 0.9; zirconium 0 to 0.25; at least one other grain-controlling element 0 to 0.5; nickel 0 to 0.5; zinc 0 to 0.5; aluminium balance (except for incidental impurities), wherein the other grain-controlling elements are selected from hafnium, niobium, scandium, cerium, chromium, titanium and vanadium, and wherein at least one of (i) manganese, (ii) zirconium and (iii) one of the said other grain controlling elements is present, (b) hot rolling the billet to produce an intermediate shape suitable for annealing, (c) annealing the said intermediate shape at a temperature sufficiently high for the intermediate shape to be softened sufficiently to be subsequently rolled, and high enough for essentially no delta ' precipitate to be formed, but not so high as to form any significant amount of C phase, and for a time sufficient to precipitate any soluble constituents therein to an extent sufficient to decrease significantly the extent of work hardening needed in step (d), (d) cold rolling the annealed intermediate shape to an extent sufficient to cause an essentially fully recrystallised grain structure to be formed therein during step (e) and to produce a sheet or strip of the desired thickness, and (e) rapidly heating and rapidly cooling the cold rolled sheet or strip material to produce an essentially fully recrystallised grain structure therein. The preferred temperature range for the annealing step (c) is from 270 DEG C to 350 DEG C.
    • 本发明涉及含锂的铝合金,其特别适用于航空航天结构,因为它们具有可选地具有改善的损伤损失的改进的冷轧特性。 描述了一种生产片材或带状材料的方法,其包括以下步骤:(a)以适合于热轧的条件提供组合物的合金重量百分比:1.9-2.6的锂; 镁0.4〜1.4; 铜1.0至2,2; 锰0〜0.9; 0至0.25的锆; 至少一个其他颗粒控制元件0至0.5; 镍0〜0.5; 锌0〜0.5; 铝平衡(偶然杂质除外),其他晶粒控制元素选自铪,铌,钪,铈,铬,钛和钒,并且其中,(i)锰,(ii)锆和( iii)存在所述其他颗粒控制元件之一,(b)热轧坯料以产生适于退火的中间形状,(c)在足够高的中等形状的温度下对所述中间形状进行退火以使其充分软化 随后被轧制,并且足够高以至于基本上没有形成δ'沉淀物,但不高到形成任何显着量的C相,并且足以使其中的任何可溶性成分沉淀到足以显着降低的程度 步骤(d)中所需的加工硬化程度,(d)将退火的中间体冷轧至足以引起基本上完全重结晶的晶粒结构的程度b 在步骤(e)中形成,并产生所需厚度的片材或条带,以及(e)快速加热和快速冷却冷轧片材或带状材料以在其中产生基本上完全再结晶的晶粒结构。 退火步骤(c)的优选温度范围为270℃至350℃。