首页> 外文会议>Conference on Metallurgists >(AerospaceBook)HOT WORKABILITY OF HIGH STRENGTH ALUMINUM AIRCRAFT ALLOYS
【24h】

(AerospaceBook)HOT WORKABILITY OF HIGH STRENGTH ALUMINUM AIRCRAFT ALLOYS

机译:(航空航天)高强度铝飞机合金的热可加工性

获取原文

摘要

The alloy additions in 2000, 7000 and 8000 series alloys, that are able to induce (from suitablecomplex heat treatments) high strength and toughness for strenuous aircraft applications, can also producewide variations in hot workability due to different sizes and distributions of precipitates that usually differconsiderably from those that are optimum for service. Precipitation during a rolling schedule from 500 to300°C poses little problem, but in extrusion dynamic precipitation in a solution-treated billet preheated at300 C, noticeably raises the initial pressure. The use of extrusion chamber deformation heating to about500°C for solution followed by quenching of the extrudate is not usually satisfactory because of the highquench sensitivity. Characteristic flow curves are presented for selected ranges of pretreatment andstraining conditions; the dependence of peak hot strength and ductility on temperature and strain rate aretabulated along with compositions as a means of estimating hot workability for new alloys, such asemployed in the Airbus 380. Comparisons are made with high strength 6000 and 5000 series alloys. Thehot workability of precipitation hardening Al alloys is particularly challenging because the hot formingtemperature range extends down from the solvus to the traditional aging temperature with 20 C providingsolute immobility. Depending on the initial precipitation condition, there is thus the potential in anyisothermal deformation for precipitation, dissolution or coalescence (or all in sequence) to take place ataccelerated rates, although the normal duration for rolling to 90% reduction or extrusion to ratio 40 mayrange from 0.5 to 50 s at rates of 0.1 to 20 s~(-1). At mid century a start was made in understandingconstitutive relations and microstructural mechanisms. By the turn of the century, testing techniques fordetermining such behaviors were readily available so that many new alloys were successfully developedfor the Airbus 380.
机译:2000,7000和8000系列合金的合金添加剂,能够诱导(从SuitereComplemplemper热处理)的高强度和韧性,用于剧烈的飞机应用,也可以在通常不同的沉淀和沉淀物的分布产生的热可加工性的变化,这通常是不同的从最佳服务的那些。从500至300℃的滚动时间表中沉淀造成很少的问题,但在预热的溶液处理的坯料中的挤出动态沉淀中,明显提高初始压力。使用挤出室变形加热至约500℃的溶液,然后淬灭由于高QueCum敏感性而不是令人满意的。为选定的预处理条件的所选范围提出了特征流程曲线;峰值热强度和延展性对温度和应变速率的依积性以及组合物作为估计新合金的热可加工性的手段,如空中客车380中的比较。用高强度6000和5000系列合金制造比较。沉淀硬化Al合金的HOT的可加工性特别具有挑战性,因为热的形成温度范围从溶解到传统的老化温度延伸到20℃的溶剂温度。因此,根据初始沉淀条件,因此存在沉淀,溶解或聚结(或所有序列)的任何潜在热变形的潜力,尽管滚动到90%的正常持续时间或挤出到比率40marmange 0.5至50秒,速率为0.1至20 s〜(-1)。在中世纪,一开始就是在理解的关系和微观结构机制中取出。到本世纪之交,可以随时可获得预防这些行为的测试技术,以便为空中客车380成功开发了许多新的合金。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱:kefu@zhangqiaokeyan.com

京公网安备:11010802029741号 ICP备案号:京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有
  • 客服微信

  • 服务号