公开(公告)号：JP2002053925A

公开(公告)日：2002-02-19

申请号：JP2001177711

申请日：2001-06-12

Applicant: ALCOA INC

Inventor： RIOJA ROBERTO J ,  WESTERLUND ROBERT W ,  ROBERTS ANNE E ,  CHAKRABARTI DHRUBA J ,  DENZER DIANA K ,  MORALES ANTHONY ,  MAGNUSEN PAUL E ,  VENEMA GREGORY B

IPC: B21B3/00 ,  C22C21/02 ,  C22C21/06 ,  C22C21/08 ,  C22C21/10 ,  C22C21/12 ,  C22C21/16 ,  C22C21/18 ,  C22F1/00 ,  C22F1/04 ,  C22F1/047 ,  C22F1/05 ,  C22F1/053 ,  C22F1/057

Abstract: PROBLEM TO BE SOLVED: To produce an aluminum alloy rolled thin sheet product having the combination of improved fatigue crack growing resistance, improved strength and fracture toughness and useful for the use for aerospace such as the airframe of aircraft and to provide its production method. SOLUTION: This aluminum alloy rolled thin sheet product has a microstructure specified by crystal grains having the average aspect ratio of the average length to width higher than about 4:1. By the control of the alloy composition, the limitation of the parameters in rolling and heat treatment, their combination or the like respectively as for an aluminum-copper-based alloy, an aluminum-magnesium-based alloy, an aluminum-magnesium-silicon-based alloy and an aluminum-zinc-based alloy, the prescribed aspect ratio, the microstructure having high anisotropy and improved quality characteristics are realized. More concretely, for developing a desired amount of precipitates, the composition of the alloy, the rolling method and the heat treating method are controlled.

公开(公告)号：WO02099151A3

公开(公告)日：2003-02-27

申请号：PCT/US0127331

申请日：2001-08-31

Applicant: ALCOA INC ,  MAGNUSEN PAUL E ,  CHAKRABARTI DHRUBA J

Inventor： MAGNUSEN PAUL E ,  CHAKRABARTI DHRUBA J

IPC: C22F1/05

CPC classification number: C22F1/05 ,  Y10T428/12764

Abstract: A process for improving 6XXX alloys, such as 6013, preferably includes heating, hot rolling, inter-rolling thermal treatment at a very high temperature such as 1020 DEG F or more, again hot rolling (with or without subsequent continuous hot rolling or cold rolling or both), solution heat treating and artificial aging. The initial heating, inter-rolling, thermal treatment and solution treatment, especially the latter two, are carried out at very high temperatures such as 1030 DEG F. Each aforesaid hot rolling stage produces substantial metal thickness reduction. The improved sheet or plate product has a substantially reduced occurrence of reduced density features revealed in scanning electron microscope examination at 500X and exhibits improved (reduced) fatigue crack growth rate providing an advantage in aerospace applications such as fuselage skin, especially fuselage belly skin.

Abstract translation: 改进6XXX合金（例如6013）的方法优选包括加热，热轧，在非常高的温度（如1020°F或更高）下进行的热轧，再次热轧（连续或不用连续的热轧或冷轧 或两者），溶解热处理和人造时效。 最初的加热，交联，热处理和固溶处理，特别是后两种，在非常高的温度例如1030°F下进行。每个上述热轧阶段都产生大量的金属厚度的减少。 改进的片材或板材产品在500X扫描电子显微镜检查中显示的减少的密度特征显着降低，并且显示改善的（降低的）疲劳裂纹扩展速率，这在航空航天应用如机身皮肤，特别是机身腹部皮肤中提供优点。

公开(公告)号：CA2731833A1

公开(公告)日：2010-02-11

申请号：CA2731833

申请日：2009-08-05

Applicant: ALCOA INC

Inventor： LI MING ,  MARINELLI JAMES M ,  LIU JIANTAO ,  MAGNUSEN PAUL E ,  SHEU SIMON ,  HEINIMANN MARKUS B ,  LIU JOHN ,  VEGA LUIS FANOR ,  FRIDEZ JEAN-DANIEL

IPC: F15D1/12 ,  B21B1/22

Abstract: Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing these metal sheets and plates are disclosed herein. In an embodiment, there is provided a transportation vessel that includes at least one metal product having at least one surface that is substantially grooved, wherein the substantially grooved surface forms a riblet topography, the riblet topography including a multiplicity of adjacent permanently rolled longitudinal riblets running along at least a part of the surface, and wherein the riblet topography is coated with at least one coating sufficiently designed and applied to preserve the riblet topography. In an embodiment, the multiplicity of adjacent permanently rolled longitudinal riblets results in a friction-reducing textured surface. In an embodiment, metal product is used in fabricating at least a portion of an aircraft. In an embodiment, metal product is used in fabricating at least a portion of a rotor blade.

公开(公告)号：CA2572232A1

公开(公告)日：2007-03-07

申请号：CA2572232

申请日：2006-09-07

Applicant: ALCOA INC

Inventor： LIN JEN C ,  BRAY GARY H ,  MAGNUSEN PAUL E ,  NEWMAN JOHN M

IPC: C22C21/18 ,  B64C1/00 ,  C22F1/057

Abstract: The invention provides a 2000 series aluminum alloy having enhanced damage tolerance, the alloy consisting essentially of about 3.0-4.0 wt % copper; about 0.4-1.1 wt % magnesium; up to about 0.8 wt % silver; up to about 1.0 wt % Zn; up to about 0.25 wt % Zr; up to about 0.9 wt % Mn; up to about 0.5 wt % Fe; and up to about 0.5 wt % Si, the balance substantially aluminum, incidental impurities and elements, said copper and magnesium present in a ratio of about 3.6-5 parts copper to about 1 part magnesium. The alloy is suitable for use in wrought or cast products including those used in aerospace applications, particularly sheet or plate structural members, extrusions and forgings, and provides an improved combination of strength and damage tolerance.

公开(公告)号：DE60108382T2

公开(公告)日：2005-12-29

申请号：DE60108382

申请日：2001-06-01

Applicant: ALCOA INC

Inventor： MAGNUSEN PAUL E ,  COLVIN EDWARD L ,  RIOJA ROBERTO J

IPC: B64C1/00 ,  C22C21/02 ,  C22C21/08 ,  C22C21/14 ,  C22C21/16 ,  C22F1/05 ,  C22F1/18 ,  C22C21/06

Abstract: There is claimed an aerospace alloy having improved corrosion resistance performance, particularly intergranular corrosion resistance. The alloy consisting essentially of: about 0.6-1.15 wt. % silicon, about 0.6-1.0 wt. % copper, about 0.8-1.2 wt. % magnesium, about 0.55-0.86 wt. % zinc, less than about 0.1 wt. % manganese, about 0.2-0.3 wt. % chromium, the balance aluminum, incidental elements and impurities. While it is preferably made into sheet or plate product forms, it can also be extruded. Products made from this alloy exhibit at least about 5% greater yield strength and about 45% or greater resistance to intergranular corrosion attack than their 6013-T6 counterparts, as measured by average depth of corrosion after 24 hours exposure to an aqueous NaCl-H2O2 solution per ASTM Standard G110 (1992).

公开(公告)号：DE1290235T1

公开(公告)日：2003-11-27

申请号：DE01965826

申请日：2001-06-01

Applicant: ALCOA INC

Inventor： MAGNUSEN PAUL E ,  COLVIN EDWARD L ,  RIOJA ROBERTO J

IPC: B64C1/00 ,  C22C21/02 ,  C22C21/08 ,  C22C21/14 ,  C22C21/16 ,  C22F1/05 ,  C22F1/18 ,  C22C21/06

Abstract: There is claimed an aerospace alloy having improved corrosion resistance performance, particularly intergranular corrosion resistance. The alloy consisting essentially of: about 0.6-1.15 wt. % silicon, about 0.6-1.0 wt. % copper, about 0.8-1.2 wt. % magnesium, about 0.55-0.86 wt. % zinc, less than about 0.1 wt. % manganese, about 0.2-0.3 wt. % chromium, the balance aluminum, incidental elements and impurities. While it is preferably made into sheet or plate product forms, it can also be extruded. Products made from this alloy exhibit at least about 5% greater yield strength and about 45% or greater resistance to intergranular corrosion attack than their 6013-T6 counterparts, as measured by average depth of corrosion after 24 hours exposure to an aqueous NaCl-H2O2 solution per ASTM Standard G110 (1992).

公开(公告)号：CA2448611A1

公开(公告)日：2002-12-12

申请号：CA2448611

申请日：2001-08-31

Applicant: ALCOA INC

Inventor： MAGNUSEN PAUL E ,  CHAKRABARTI DHRUBA J

IPC: C22F1/05

Abstract: A process for improving 6XXX alloys, such as 6013, preferably includes heating, hot rolling, inter-rolling thermal treatment at a very high temperature such as 1020 ~F or more, again hot rolling (with or without subsequent continuous hot rolling or cold rolling or both), solution heat treating and artificial aging. The initial heating, inter-rolling, thermal treatment and solution treatment, especially the latter two, are carried out at very high temperatures such as 1030 ~F. Each aforesaid hot rolling stage produces substantial metal thickness reduction. The improved sheet or plate product has a substantially reduced occurrence of reduced density features revealed in scanning electron microscope examination at 500X and exhibits improved (reduced) fatigue crack growth rate providing an advantage in aerospace applications such as fuselage skin, especially fuselage belly skin .

公开(公告)号：WO2007111634A3

公开(公告)日：2007-12-06

申请号：PCT/US2006034664

申请日：2006-09-07

Applicant: ALCOA INC ,  LIN JEN C ,  NEWMAN JOHN M ,  MAGNUSEN PAUL E ,  BRAY GARY H

Inventor： LIN JEN C ,  NEWMAN JOHN M ,  MAGNUSEN PAUL E ,  BRAY GARY H

IPC: C22C21/12 ,  C22C21/14

CPC classification number: C22C21/12 ,  C22C1/06 ,  C22C21/14 ,  C22C21/16

Abstract: The invention provides a 2000 series aluminum alloy having enhanced damage tolerance, the alloy consisting essentially of about 3.0-4.0 wt% copper; about 0.4-1.1 wt% magnesium; up to about 0.8 wt% silver; up to about 1.0 wt% Zn; up to about 0.25 wt% Zr; up to about 0.9 wt% Mn; up to about 0.5 wt% Fe; and up to about 0.5 wt% Si, the balance substantially aluminum, incidental impurities and elements, said copper and magnesium present in a ratio of about 3.6-5 parts copper to about 1 part magnesium. The alloy is suitable for use in wrought or cast products including those used in aerospace applications, particularly sheet or plate structural members, extrusions and forgings, and provides an improved combination of strength and damage tolerance.

Abstract translation: 本发明提供了具有增强的耐损伤性的2000系列铝合金，该合金基本上由约3.0-4.0重量％的铜组成; 约0.4-1.1重量％的镁; 至多约0.8重量％的银; 至多约1.0重量％的Zn; 至多约0.25重量％的Zr; 至多约0.9重量％的Mn; 至多约0.5重量％的Fe; 和至多约0.5重量％的Si，余量基本上为铝，附带的杂质和元素，所述铜和镁以约3.6-5份铜与约1份镁的比例存在。 该合金适用于锻造或铸造产品，包括在航空航天应用中使用的那些产品，特别是板材或板材结构件，挤压件和锻件，并提供强度和损伤公差的改进组合。

公开(公告)号：WO2006019946A2

公开(公告)日：2006-02-23

申请号：PCT/US2005025047

申请日：2005-07-14

Applicant: ALCOA INC

Inventor： LIN JEN C ,  NEWMAN JOHN M ,  MAGNUSEN PAUL E ,  BRAY GARY H

IPC: C22C21/12

CPC classification number: C22C21/14 ,  C22C1/06 ,  C22C21/12 ,  C22C21/16 ,  C22F1/057

Abstract: The invention provides a 2000 series aluminum alloy having enhanced damage tolerance, the alloy consisting essentially of about 3.0-4.0 wt% copper; about 0.4-1.1 wt% magnesium; up to about 0.8 wt% silver; up to about 1.0 wt% Zn; up to about 0.25 wt% Zr; up to about 0.9 wt% Mn; up to about 0.5 wt% Fe; and up to about 0.5 wt% Si, the balance substantially aluminum, incidental impurities and elements, said copper and magnesium present in a ratio of about 3.6-5 parts copper to about 1 part magnesium. The alloy is suitable for use in wrought or cast products including those used in aerospace applications, particularly sheet or plate structural members, extrusions and forgings, and provides an improved combination of strength and damage tolerance.

Abstract translation: 本发明提供了具有增强的耐损伤性的2000系列铝合金，该合金基本上由约3.0-4.0重量％的铜组成; 约0.4-1.1重量％的镁; 至多约0.8重量％的银; 至多约1.0重量％的Zn; 至多约0.25重量％的Zr; 至多约0.9重量％的Mn; 至多约0.5重量％的Fe; 和至多约0.5重量％的Si，余量基本上为铝，附带的杂质和元素，所述铜和镁以约3.6-5份铜与约1份镁的比例存在。 该合金适用于锻造或铸造产品，包括在航空航天应用中使用的那些产品，特别是板材或板材结构件，挤压件和锻件，并提供强度和损伤公差的改进组合。

公开(公告)号：WO0192591A3

公开(公告)日：2002-05-30

申请号：PCT/US0117803

申请日：2001-06-01

Applicant: ALCOA INC ,  MAGNUSEN PAUL E ,  COLVIN EDWARD L ,  RIOJA ROBERTO J

Inventor： MAGNUSEN PAUL E ,  COLVIN EDWARD L ,  RIOJA ROBERTO J

IPC: B64C1/00 ,  C22C21/02 ,  C22C21/08 ,  C22C21/14 ,  C22C21/16 ,  C22F1/05 ,  C22F1/18 ,  C22C21/06

CPC classification number: C22C21/16 ,  C22C21/02 ,  C22C21/08 ,  C22C21/14 ,  C22F1/05 ,  C22F1/183 ,  Y10T428/12764

Abstract: There is claimed an aerospace alloy having improved corrosion resistance performance, particularly intergranular corrosion resistance. The alloy consisting essentially of: about 0.6-1.15 wt. % silicon, about 0.6-1.0 wt. % copper, about 0.8-1.2 wt. % magnesium, about 0.55-0.86 wt. % zinc, less than about 0.1 wt. % manganese, about 0.2-0.3 wt. % chromium, the balance aluminum, incidental elements and impurities. While it is preferably made into sheet or plate product forms, it can also be extruded. Products made from this alloy exhibit at least about 5 % greater yield strength and about 45 % or greater resistance to intergranular corrosion attack than their 6013-T6 counterparts, as measured by average depth of corrosion after 24 hours exposure to an aqueous NaCl-H>2 2

Abstract translation: 要求具有改进的耐腐蚀性能，特别是耐晶间腐蚀性的航空合金。 该合金基本上由以下组成：约0.6-1.15重量％ ％硅，约0.6-1.0wt。 ％铜，约0.8-1.2重量％ ％镁，约0.55-0.86重量％ ％锌，小于约0.1wt。 ％锰，约0.2-0.3重量％ ％铬，余量为铝，附带元素和杂质。 虽然优选制成片材或板材产品形式，但也可以挤出。 由该合金制成的产品比其6013-T6对应物具有至少约5％的屈服强度和约45％或更大的耐晶间腐蚀侵蚀性，如通过暴露于NaCl-H>水溶液24小时后的平均腐蚀深度所测量的， 2 2 <溶液/ ASTM标准G110（1992）。