公开(公告)号：US20150368773A1

公开(公告)日：2015-12-24

申请号：US14607912

申请日：2015-01-28

Applicant: ALCOA INC.

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

IPC: C22F1/053 ,  C22C21/10

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

Abstract: 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.

Abstract translation: 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：US08961715B2

公开(公告)日：2015-02-24

申请号：US14255536

申请日：2014-04-17

Applicant: Alcoa Inc.

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

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

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

Abstract: 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.

Abstract translation: 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：US20140227131A1

公开(公告)日：2014-08-14

申请号：US14255536

申请日：2014-04-17

Applicant: ALCOA INC.

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

IPC: C22C21/10

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

Abstract: 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.

Abstract translation: 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：US20140050936A1

公开(公告)日：2014-02-20

申请号：US13785793

申请日：2013-03-05

Applicant: ALCOA INC.

Inventor： Julien Boselli ,  Roberto J. Rioja ,  Gregory B. Venema ,  Ralph R. Sawtell ,  Paul E. Magnusen

IPC: C22C21/18 ,  C22C21/16 ,  C22C21/14

CPC classification number: C22C21/18 ,  C22C21/14 ,  C22C21/16 ,  C22F1/057 ,  Y10T428/12

Abstract: Wrought 2xxx aluminum lithium alloy products having a thickness of from 0.040 inch to 0.500 inch are disclosed. The wrought aluminum alloy products contain from 3.00 to 3.80 wt. % Cu, from 0.05 to 0.35 wt. % Mg, from 0.975 to 1.385 wt. % Li, wherein −0.3*Mg−0.15Cu+1.65≦Li≦−0.3*Mg−0.15Cu+1.85, from 0.05 to 0.50 wt. % of at least one grain structure control element, wherein the grain structure control element is selected from the group consisting of Zr, Sc, Cr, V, Hf, other rare earth elements, and combinations thereof, up to 1.0 wt. % Zn, up to 1.0 wt. % Mn, up to 0.12 wt. % Si, up to 0.15 wt. % Fe, up to 0.15 wt. % Ti, up to 0.10 wt. % of any other element, with the total of these other elements not exceeding 0.35 wt. %, the balance being aluminum.

Abstract translation: 公开了厚度为0.040英寸至0.500英寸的锻造2xxx铝锂合金产品。 锻造的铝合金产品含有3.00〜3.80重量％ ％Cu，0.05〜0.35wt。 ％Mg，0.975〜1.385wt。 ％Li，其中-0.3 * Mg-0.15Cu + 1.65 @ Li @ -0.3 * Mg-0.15Cu + 1.85，0.05-0.50wt。 ％的至少一种晶粒结构控制元素，其中所述晶粒结构控制元素选自Zr，Sc，Cr，V，Hf，其它稀土元素及其组合，最多为1.0wt。 ％Zn，至多1.0wt。 ％Mn，高达0.12wt。 ％Si，至多0.15wt。 ％Fe，至多0.15wt。 ％Ti，至多0.10wt。 任何其他元素的百分比，其中这些其他元素的总和不超过0.35重量％。 ％，余量为铝。

公开(公告)号：US20140248176A1

公开(公告)日：2014-09-04

申请号：US14283024

申请日：2014-05-20

Applicant: ALCOA INC.

Inventor： Jen C. Lin ,  Ralph R. Sawtell ,  Gary H. Bray ,  Cindie Giummarra ,  Andre Wilson ,  Gregory B. Venema

IPC: C22C21/16

Abstract: New 2xxx aluminum alloys containing vanadium are disclosed. In one embodiment, the aluminum alloy includes 3.3-4.1 wt. % Cu, 0.7-1.3 wt. % Mg, 0.01-0.16 wt. % V, 0.05-0.6 wt. % Mn, 0.01 to 0.4 wt. % of at least one grain structure control element, the balance being aluminum, incidental elements and impurities. The new alloys may realize an improved combination of properties, such as in the T39 or T89 tempers.

公开(公告)号：US10450640B2

公开(公告)日：2019-10-22

申请号：US13962696

申请日：2013-08-08

Applicant: ALCOA INC.

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

IPC: C22F1/053 ,  B22D17/22 ,  C22C21/10

Abstract: 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.

公开(公告)号：US20130312877A1

公开(公告)日：2013-11-28

申请号：US13962696

申请日：2013-08-08

Applicant: ALCOA INC.

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

IPC: C22F1/053

CPC classification number: C22F1/053 ,  B22D17/2209 ,  C22C21/10

Abstract: 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.

Abstract translation: 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。