公开(公告)号：US06562154B1

公开(公告)日：2003-05-13

申请号：US09591904

申请日：2000-06-12

申请人： Roberto J. Rioja ,  Robert W. Westerlund ,  Anne E. Roberts ,  Dhruba J. Chakrabarti ,  Diana K. Denzer ,  Anthony Morales ,  Paul E. Magnusen ,  Gregory B. Venema

发明人： Roberto J. Rioja ,  Robert W. Westerlund ,  Anne E. Roberts ,  Dhruba J. Chakrabarti ,  Diana K. Denzer ,  Anthony Morales ,  Paul E. Magnusen ,  Gregory B. Venema

IPC分类号： C22C2100

CPC分类号： C22F1/057 ,  C22C21/02 ,  C22C21/08 ,  C22C21/10 ,  C22C21/16 ,  C22F1/04 ,  C22F1/05 ,  C22F1/053

摘要： Aluminum sheet products having highly anisotropic grain microstructures and highly textured crystallographic microstructures are disclosed. The products exhibit improved strength and improved resistance to fatigue crack growth, as well as other advantageous properties such as improved combinations of strength and fracture toughness. The sheet products are useful for aerospace and other applications, particularly aircraft fuselages.

摘要翻译： 公开了具有高度各向异性颗粒微结构和高度纹理化的结晶微结构的铝板产品。 产品具有改进的强度和改善的抗疲劳裂纹生长性能，以及其它有利的性能，例如改进的强度和断裂韧性的组合。 片材产品可用于航空航天和其他应用，特别是飞机机身。

公开(公告)号：US08840737B2

公开(公告)日：2014-09-23

申请号：US12152635

申请日：2008-05-14

申请人： Gary H. Bray ,  Dhruba J. Chakrabarti ,  Diana K. Denzer ,  Jen C. Lin ,  John Newman ,  Gregory B. Venema ,  Cagatay Yanar ,  Julien Boselli

发明人： Gary H. Bray ,  Dhruba J. Chakrabarti ,  Diana K. Denzer ,  Jen C. Lin ,  John Newman ,  Gregory B. Venema ,  Cagatay Yanar ,  Julien Boselli

IPC分类号： C22C21/10 ,  B64C3/26 ,  C22F1/053 ,  B64C3/18 ,  B64C1/00

CPC分类号： C22F1/053 ,  B64C3/182 ,  B64C3/185 ,  B64C3/187 ,  B64C3/26 ,  B64C2001/0081 ,  C22C21/10 ,  Y02T50/42

摘要： Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The instantly disclosed alloys are useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction.

摘要翻译： 约4英寸厚或以下的铝合金产品具有在固溶热处理，淬火和人工老化的同时实现的能力，以及由产品制成的零件中，改进了强度，断裂韧性和耐腐蚀性的组合，该合金组成 基本上为：约6.8至约8.5wt。 ％Zn，约1.5至约2.00wt。 ％Mg，约1.75至约2.3wt。 ％Cu; 约0.05至约0.3wt。 ％Zr，小于约0.1wt。 ％Mn，小于约0.05wt。 ％Cr，余量为Al，附带元素和杂质及其制备方法。 瞬时公开的合金可用于制造商用飞机的结构构件，包括但不限于上部翼皮和桁条，翼梁盖，翼梁腹板和构成或整体结构的肋。

公开(公告)号：US07678205B2

公开(公告)日：2010-03-16

申请号：US11287744

申请日：2005-11-28

申请人： Dhruba J. Chakrabarti ,  John Liu ,  Jay H. Goodman ,  Gregory B. Venema ,  Ralph R. Sawtell ,  Cynthia M. Krist ,  Robert W. Westerlund

发明人： Dhruba J. Chakrabarti ,  John Liu ,  Jay H. Goodman ,  Gregory B. Venema ,  Ralph R. Sawtell ,  Cynthia M. Krist ,  Robert W. Westerlund

IPC分类号： C22C21/10

CPC分类号： C22F1/053 ,  B22D17/2209 ,  C22C21/10

摘要： Aluminum alloy products, such as plate, forgings and extrusions, suitable for use in making aerospace structural components like integral wing spars, ribs and webs, comprises about: 6 to 10 wt. % Zn; 1.2 to 1.9 wt. % Mg; 1.2 to 2.2 wt. % Cu, with Mg≦(Cu+0.3); and 0.05 to 0.4 wt. % Zr, the balance Al, incidental elements and impurities. Preferably, the alloy contains about 6.9 to 8.5 wt. % Zn; 1.2 to 1.7 wt. % Mg; 1.3 to 2 wt. % Cu. This alloy provides improved combinations of strength and fracture toughness in thick gauges. When artificially aged per the three stage method of preferred embodiments, this alloy also achieves superior SCC performance, including under seacoast conditions.

摘要翻译： 适合用于制造航空航天结构部件如整体翼梁，肋骨和腹板的铝合金产品，例如板，锻件和挤压件，包括：约6至10wt。 ％Zn; 1.2〜1.9重量％ ％Mg; 1.2〜2.2重量％ ％Cu，Mg + NlE;（Cu + 0.3）; 和0.05〜0.4重量％ ％Zr，余量为Al，附带元素和杂质。 优选地，合金含有约6.9至8.5wt。 ％Zn; 1.2〜1.7重量％ ％Mg; 1.3〜2重量％ ％Cu。 该合金提供了厚度计中强度和断裂韧性的改进组合。 当根据优选实施方案的三阶段方法人工老化时，该合金还实现了优异的SCC性能，包括在海岸条件下。

公开(公告)号：US20100037998A1

公开(公告)日：2010-02-18

申请号：US12152635

申请日：2008-05-14

申请人： Gary H. Bray ,  Dhruba J. Chakrabarti ,  Diana K. Denzer ,  Jen C. Lin ,  John Newman ,  Gregory B. Venema ,  Cagatay Yanar ,  Julien Boselli

发明人： Gary H. Bray ,  Dhruba J. Chakrabarti ,  Diana K. Denzer ,  Jen C. Lin ,  John Newman ,  Gregory B. Venema ,  Cagatay Yanar ,  Julien Boselli

IPC分类号： C22F1/053 ,  C22C21/10

CPC分类号： C22F1/053 ,  B64C3/182 ,  B64C3/185 ,  B64C3/187 ,  B64C3/26 ,  B64C2001/0081 ,  C22C21/10 ,  Y02T50/42

摘要： Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The instantly disclosed alloys are useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction.

摘要翻译： 约4英寸厚或以下的铝合金产品具有在固溶热处理，淬火和人工老化的同时实现的能力，以及由产品制成的零件中，改进了强度，断裂韧性和耐腐蚀性的组合，该合金组成 基本上为：约6.8至约8.5wt。 ％Zn，约1.5至约2.00wt。 ％Mg，约1.75至约2.3wt。 ％Cu; 约0.05至约0.3wt。 ％Zr，小于约0.1wt。 ％Mn，小于约0.05wt。 ％Cr，余量为Al，附带元素和杂质及其制备方法。 瞬时公开的合金可用于制造商用飞机的结构构件，包括但不限于上部翼皮和桁条，翼梁盖，翼梁腹板和构成或整体结构的肋。

公开(公告)号：US5810949A

公开(公告)日：1998-09-22

申请号：US473827

申请日：1995-06-07

申请人： Dhruba J. Chakrabarti ,  Robert W. Westerlund ,  Bruce A. Halter

发明人： Dhruba J. Chakrabarti ,  Robert W. Westerlund ,  Bruce A. Halter

IPC分类号： C22C1/057

CPC分类号： C22C1/02

摘要： A method is disclosed for treating an aluminum alloy product in order to impart a fine grain structure and thereby improve formability and surface finish characteristics. According to this method, the product is first heated to a first temperature high enough to dissolve soluble constituent phase particles into solid solution. The product is maintained at this first temperature long enough to dissolve a major portion of the soluble constituent phase particles. Thereafter, the product is subjected to a controlled cooling process. The product is first cooled from the first temperature, at a first rate that is rapid enough to minimize the precipitation of coarse-grained constituent phase particles, to a second temperature that is below the temperature at which such coarse-grained constituent phase particles will precipitate out. Then, the product is cooled from the second temperature, at a second rate that is within a range of about 1-300 degrees F. per hour, to a third temperature that is at least 50 degrees F. below the second temperature. After the temperature of the product has been reduced to the third temperature, the product is cold worked. After cold working, the temperature of the product is raised to a fourth temperature sufficient to cause recrystallization of the product. The product so treated will exhibit improved formability and surface characteristics, and may exhibit an average grain size of less than about 30 microns.

摘要翻译： 公开了一种用于处理铝合金产品以提供细晶粒结构，从而提高成形性和表面光洁度特性的方法。 根据该方法，首先将产物加热到足够高的第一温度以将可溶组分相颗粒溶解成固溶体。 产物在该第一温度下保持足够长的时间以溶解主要部分的可溶性组成相颗粒。 此后，对产品进行受控制的冷却过程。 首先将产物从第一个温度以足够快的速度将粗粒子组成相颗粒的沉淀最小化到低于这种粗粒组成相颗粒将沉淀的温度的第二温度 出来 然后，将产品从第二温度以约1-300°F /小时的第二速率冷却至低于第二温度至少50°F的第三温度。 产品的温度降低到第三个温度后，产品冷加工。 冷加工后，将产品的温度升至足以引起产品再结晶的第四温度。 如此处理的产品将具有改进的成形性和表面特性，并且可以显示出小于约30微米的平均晶粒尺寸。

公开(公告)号：US5747135A

公开(公告)日：1998-05-05

申请号：US569344

申请日：1995-12-08

申请人： Dhruba J. Chakrabarti ,  Richard A. Hoffman ,  Craig L. Jensen

发明人： Dhruba J. Chakrabarti ,  Richard A. Hoffman ,  Craig L. Jensen

IPC分类号： G11B5/73 ,  B32B3/00

CPC分类号： G11B5/7325 ,  Y10S428/913

摘要： A memory media-ready substrate having a substrate, a hardening layer and a film made of a nonferromagnetic material that is disposed between the substrate and the film. A memory disk including the film and associated methods of making a hardening layer-ready substrate, the memory media-ready substrate and the memory disk are also provided.

摘要翻译： 具有衬底，硬化层和由非铁磁材料制成的膜的存储介质就绪衬底，其设置在衬底和膜之间。 还提供了包括该薄膜的存储盘以及制备硬化层就绪衬底，存储介质就绪衬底和存储盘的相关方法。

公开(公告)号：US08524014B2

公开(公告)日：2013-09-03

申请号：US13178339

申请日：2011-07-07

申请人： Dhruba J. Chakrabarti ,  John Liu ,  Jay H. Goodman ,  Gregory B. Venema ,  Ralph R. Sawtell ,  Cynthia M. Krist ,  Robert W. Westerlund

发明人： Dhruba J. Chakrabarti ,  John Liu ,  Jay H. Goodman ,  Gregory B. Venema ,  Ralph R. Sawtell ,  Cynthia M. Krist ,  Robert W. Westerlund

IPC分类号： C22C21/10

CPC分类号： C22F1/053 ,  B22D17/2209 ,  C22C21/10

摘要： Aluminum alloy products, such as plate, forgings and extrusions, suitable for use in making aerospace structural components like integral wing spars, ribs and webs, comprises about: 6 to 10 wt. % Zn; 1.2 to 1.9 wt. % Mg; 1.2 to 2.2 wt. % Cu, with Mg≦(Cu+0.3); and 0.05 to 0.4 wt. % Zr, the balance Al, incidental elements and impurities. Preferably, the alloy contains about 6.9 to 8.5 wt. % Zn; 1.2 to 1.7 wt. % Mg; 1.3 to 2 wt. % Cu. This alloy provides improved combinations of strength and fracture toughness in thick gauges. When artificially aged per the 3-stage method of preferred embodiments, this alloy also achieves superior SCC performance, including under seacoast conditions.

摘要翻译： 适合用于制造航空航天结构部件如整体翼梁，肋骨和腹板的铝合金产品，例如板，锻件和挤压件，包括：约6至10wt。 ％Zn; 1.2〜1.9重量％ ％Mg; 1.2〜2.2重量％ ％Cu，Mg @（Cu + 0.3）; 和0.05〜0.4重量％ ％Zr，余量为Al，附带元素和杂质。 优选地，合金含有约6.9至8.5wt。 ％Zn; 1.2〜1.7重量％ ％Mg; 1.3〜2重量％ ％Cu。 该合金提供了厚度计中强度和断裂韧性的改进组合。 当根据优选实施方案的3阶段方法人工老化时，该合金还实现了优异的SCC性能，包括在海岸条件下。

公开(公告)号：US08083870B2

公开(公告)日：2011-12-27

申请号：US11052392

申请日：2005-02-07

申请人： Dhruba J. Chakrabarti ,  John Liu ,  Jay H. Goodman ,  Gregory B. Venema ,  Ralph R. Sawtell ,  Cynthia M. Krist ,  Robert W. Westerlund

发明人： Dhruba J. Chakrabarti ,  John Liu ,  Jay H. Goodman ,  Gregory B. Venema ,  Ralph R. Sawtell ,  Cynthia M. Krist ,  Robert W. Westerlund

IPC分类号： C22C21/10

CPC分类号： C22F1/053 ,  B22D17/2209 ,  C22C21/10

摘要： Aluminum alloy products, such as plate, forgings and extrusions, suitable for use in making aerospace structural components like integral wing spars, ribs and webs, comprises about: 6 to 10 wt. % Zn; 1.2 to 1.9 wt. % Mg; 1.2 to 2.2 wt. % Cu, with Mg≦(Cu+0.3); and 0.05 to 0.4 wt. % Zr, the balance Al, incidental elements and impurities. Preferably, the alloy contains about 6.9 to 8.5 wt. % Zn; 1.2 to 1.7 wt. % Mg; 1.3 to 2 wt. % Cu. This alloy provides improved combinations of strength and fracture toughness in thick gauges. When artificially aged per the three stage method of preferred embodiments, this alloy also achieves superior SCC performance, including under seacoast conditions.

摘要翻译： 适合用于制造航空航天结构部件如整体翼梁，肋骨和腹板的铝合金产品，例如板，锻件和挤压件，包括：约6至10wt。 ％Zn; 1.2〜1.9重量％ ％Mg; 1.2〜2.2重量％ ％Cu，Mg + NlE;（Cu + 0.3）; 和0.05〜0.4重量％ ％Zr，余量为Al，附带元素和杂质。 优选地，合金含有约6.9至8.5wt。 ％Zn; 1.2〜1.7重量％ ％Mg; 1.3〜2重量％ ％Cu。 该合金提供了厚度计中强度和断裂韧性的改进组合。 当根据优选实施方案的三阶段方法人工老化时，该合金还实现了优异的SCC性能，包括在海岸条件下。

公开(公告)号：US06972110B2

公开(公告)日：2005-12-06

申请号：US09971456

申请日：2001-10-04

申请人： Dhruba J. Chakrabarti ,  John Liu ,  Jay H. Goodman ,  Gregory B. Venema ,  Ralph R. Sawtell ,  Cynthia M. Krist ,  Robert W. Westerlund

发明人： Dhruba J. Chakrabarti ,  John Liu ,  Jay H. Goodman ,  Gregory B. Venema ,  Ralph R. Sawtell ,  Cynthia M. Krist ,  Robert W. Westerlund

IPC分类号： C22C21/10 ,  C22F1/00 ,  C22F1/053 ,  C22C22/00

CPC分类号： C22F1/053 ,  B22D17/2209 ,  C22C21/10

摘要： Aluminum alloy products, such as plate, forgings and extrusions, suitable for use in making aerospace structural components like integral wing spars, ribs and webs, comprises about: 6 to 10 wt. % Zn; 1.2 to 1.9 wt. % Mg; 1.2 to 2.2 wt. % Cu, with Mg≦(Cu+0.3); and 0.05 to 0.4 wt. % Zr, the balance Al, incidental elements and impurities. Preferably, the alloy contains about 6.9 to 8.5 wt. % Zn; 1.2 to 1.7 wt. % Mg; 1.3 to 2 wt. % Cu. This alloy provides improved combinations of strength and fracture toughness in thick gauges. When artificially aged per the three stage method of preferred embodiments, this alloy also achieves superior SCC performance, including under seacoast conditions.

摘要翻译： 适合用于制造航空航天结构部件如整体翼梁，肋骨和腹板的铝合金产品，例如板，锻件和挤压件，包括：约6至10wt。 ％Zn; 1.2〜1.9重量％ ％Mg; 1.2〜2.2重量％ ％Cu，Mg <=（Cu + 0.3）; 和0.05〜0.4重量％ ％Zr，余量为Al，附带元素和杂质。 优选地，合金含有约6.9至8.5wt。 ％Zn; 1.2〜1.7重量％ ％Mg; 1.3〜2重量％ ％Cu。 该合金提供了厚度计中强度和断裂韧性的改进组合。 当根据优选实施方案的三阶段方法人工老化时，该合金还实现了优异的SCC性能，包括在海岸条件下。

公开(公告)号：US6063210A

公开(公告)日：2000-05-16

申请号：US919869

申请日：1997-08-28

申请人： Dhruba J. Chakrabarti ,  Roger D. Doherty

发明人： Dhruba J. Chakrabarti ,  Roger D. Doherty

IPC分类号： C22C21/06 ,  C22C21/08 ,  C22F1/047

CPC分类号： C22F1/047 ,  C22C21/06 ,  C22C21/08 ,  Y10S420/902

摘要： A superplastically formable, aluminum alloy product which consists essentially of about 2-10 wt. % magnesium; at least one dispersoid-forming element selected from the group consisting of: up to about 1.6 wt. % manganese, up to about 0.2 wt. % zirconium, and up to about 0.3 w. % chromium; at least one nucleation-enhancing element for recrystallization selected from: up to about 1.0 wt. % silicon, up to about 1.5 wt. % copper, and combinations thereof. Said alloy product has greater than about 300% elongation at a strain rate of at least about 0.0003/sec and a superplastic forming temperature between about 1000-1100.degree. F. due, in part, to the preferred thermomechanical processing steps subsequently applied thereto. A related method of manufacture is also disclosed herein.

摘要翻译： 一种超塑性成型的铝合金产品，其基本上由约2-10重量％ ％镁; 至少一种选自以下的分散质形成元素：至多约1.6重量％ ％锰，至多约0.2重量％ ％锆，最高约0.3w。 ％铬; 至少一种用于重结晶的成核增强元素选自：至多约1.0wt。 ％硅，高达约1.5重量％ ％铜及其组合。 所述合金产品在至少约0.0003 /秒的应变速率下具有大于约300％的伸长率，超塑性成形温度在约1000-1100°F之间，部分归因于随后施加于其上的优选的热机械加工步骤。 本文还公开了相关的制造方法。