Patents by Inventor Philippe Lassince
Philippe Lassince has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Publication number: 20190368009Abstract: The high strength 7xxx aluminum alloy products and methods of making such products are disclosed resulting in better fatigue crack deviation performance, and high anisotropic ductility. The 7xxx aluminum alloy product comprises 7.0 to 7.8 wt. % Zn, 1.1 to 2.2 wt. % Cu, and 1.1 to 2.1 wt. % Mg. This 7xxx aluminum alloy product can be fabricated to produce plate, extrusion or forging products, and is especially suitable for aerospace structural components, especially large commercial airplane wing structure applications. The minimum tensile yield strength (TYS) along rolling (LT) direction is higher than 65 ksi for 4 to 5 inch plate. The minimum Kmax at crack deviation point is higher than 31 ksi*in1/2 for 4 to 5 inch plate. The minimum elongation is 1.4% for all tensile orientations including lowest orientations of ST-22.5 to ST-45. The 7xxx aluminum alloy product provides high damage tolerance performance as well as better corrosion resistance performance suitable for aerospace application.Type: ApplicationFiled: June 5, 2018Publication date: December 5, 2019Applicant: Kaiser Aluminum Fabricated Products, Inc.Inventors: Zhengdong Long, Philippe Lassince, Robert A. Matuska, Ravi Rastogi
-
Publication number: 20190233921Abstract: The present invention is directed to aluminum-lithium alloys, specifically aluminum—copper—lithium—magnesium—manganese alloys. The aluminum-lithium alloy of the present invention comprises from 3.6 to 4.1 wt. % Cu, 0.8 to 1.05 wt. % Li, 0.6 to 1.0 wt. % Mg, 0.2 to 0.6 wt. % Mn, up to 0.12 wt. % Si, up to 0.15 wt. % Fe, from 0.03 to 0.16 wt. % of at least one grain structure control element selected from the group consisting of Zr, Sc, Cr, V, Hf, and other rare earth elements, up to 0.10 wt. % Ti, up to 0.15 wt. % incidental elements with the total of incidental elements not exceeding 0.35 wt. %, and the balance being aluminum. Preferably, Ag is not intentionally added and should not be more than 0.05 wt. % as a non-intentionally added element. Preferably, Zn is not intentionally added and should not be more than 0.2 wt. % as a non-intentionally added element. The amount of Cu in weight percent is at least equal to or higher than four times the amount of Li in weight percent.Type: ApplicationFiled: February 1, 2018Publication date: August 1, 2019Applicant: Kaiser Aluminum Fabricated Products, LLCInventors: Zhengdong Long, Philippe Lassince, Robert A. Matuska, Florence Andrea Baldwin, David J. Shoemaker, Ravi Rastogi, Roy A. Nash
-
Publication number: 20190169727Abstract: A low cost, substantially Zr-free, low density 2xxx aluminum-lithium alloy is disclosed. The aluminum-lithium alloy can be produced to high formability sheet products capable of being formed into wrought products with a thickness of 0.01? to 0.249?. Aluminum-lithium alloys of the invention comprise from 3.2 to 4.1 wt. % Cu, 1.0 to 1.8 wt. % Li, 0.8 to 1.2 wt. % Mg, 0.10 to 0.50 wt. % Zn, 0.10 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 0.15 wt. % incidental elements, with the total of these incidental elements not exceeding 0.35 wt. %, and the balance being aluminum. Ag should not be intentionally added and should not be more than 0.1 wt. % as a non-intentionally added element. Zr should not be intentionally added and should not be more than 0.05 wt. % as a non-intentionally added element. Mg is at least equal to or higher than 2*Zn in weight percent in the invented alloy.Type: ApplicationFiled: December 4, 2017Publication date: June 6, 2019Applicant: Kaiser Aluminum Fabricated Products, LLCInventors: Zhengdong Long, Philippe Lassince, Robert A. Matuska, Florence Andrea Baldwin, Ravi Rastogi, Roy Austin Nash, Jason Nicholas Scheuring, Gary D. Holmesmith, Yansheng Liu
-
Patent number: 10253404Abstract: A high strength, high formability and low cost 2xxx aluminum-lithium alloy is disclosed. The aluminum-lithium alloy is capable of being formed into wrought products with a thickness of from about 0.01? to about 0.249?. Aluminum-lithium alloys of the invention generally comprise from about 3.5 to 4.5 wt. % Cu, 0.8 to 1.6 wt. % Li, 0.6 to 1.5 wt. % Mg, from 0.03 to 0.6 wt. % of at least one grain structure control element selected from the group consisting of Zr, Sc, Cr, V, Hf, and other rare earth elements, and 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 0.05 wt. % of any other element, with the total of these other elements not exceeding 0.15 wt. %, and the balance being aluminum. Ag should not be more than 0.5 wt. % and is preferably not intentionally added. Mg is at least equal or higher than Zn in weight percent in the invented alloy.Type: GrantFiled: October 26, 2014Date of Patent: April 9, 2019Assignee: Kaiser Aluminum Fabricated Products, LLCInventors: Zhengdong Long, Philippe Lassince, Florence Andrea Baldwin, Robert A. Matuska, Yansheng Liu, Roy Austin Nash, Jason Nicholas Scheuring, Gary D. Holmesmith
-
Publication number: 20160348224Abstract: The present invention is directed to a thick plate high strength 7xxx aluminum alloy product comprising 8.0 to 8.4 wt. % Zn, 1.5 to 2.0 wt. % Mg, 1.1 to 1.5 wt. % Cu, and 0.05 to 0.15 wt. % Zr, 4.0 to 5.3 of Zn/Mg weight percentage ratio, 0.14 to 0.19 of Cu/Zn weight percentage ratio, and 10.7 to 11.6 wt. % of Cu+Mg+Zn. This alloy can be fabricated to produce 3-10 inch thick plate, extrusion or forging products, and is especially suitable for aerospace structural components, especially large commercial airplane wing structure applications. The product provides high strength, high damage tolerance performance as well as better corrosion resistance performance suitable for aerospace application.Type: ApplicationFiled: June 1, 2015Publication date: December 1, 2016Applicant: KAISER ALUMINUM FABRICATED PRODUCTS, LLCInventors: Zhengdong Long, Jane Elizabeth Buehler, Florence Andrea Baldwin, Junsheng Wang, Jason Nicholas Scheuring, Philippe Lassince, Robert A. Matuska, Roy Austin Nash, Philippe Gomiero
-
Publication number: 20160115576Abstract: A high strength, high formability and low cost 2xxx aluminum-lithium alloy is disclosed. The aluminum-lithium alloy is capable of being formed into wrought products with a thickness of from about 0.01? to about 0.249?. Aluminum-lithium alloys of the invention generally comprise from about 3.5 to 4.5 wt. % Cu, 0.8 to 1.6 wt. % Li, 0.6 to 1.5 wt. % Mg, from 0.03 to 0.6 wt. % of at least one grain structure control element selected from the group consisting of Zr, Sc, Cr, V, Hf, and other rare earth elements, and 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 0.05 wt. % of any other element, with the total of these other elements not exceeding 0.15 wt. %, and the balance being aluminum. Ag should not be more than 0.5 wt. % and is preferably not intentionally added. Mg is at least equal or higher than Zn in weight percent in the invented alloy.Type: ApplicationFiled: October 26, 2014Publication date: April 28, 2016Applicant: KAISER ALUMINUM FABRICATED PRODUCTS, LLCInventors: Zhengdong Long, Philippe Lassince, Florence Andrea Baldwin, Robert A. Matuska, Yansheng Liu, Roy Austin Nash, Jason Nicholas Scheuring, Gary D. Holmesmith
-
Publication number: 20150240338Abstract: The present invention is directed to an ultra-thick high strength aluminum alloy, comprising 7.5 to 8.4 wt. % Zn, 1.6 to 2.3 wt. % Mg, 1.4 to 2.1 wt. % Cu, and 0.05 to 0.15 wt. % Zr. This alloy can be fabricated to produce 2-10 inch thick plate, extrusion or forging products, and is especially suitable for aerospace structural components, especially large commercial airplane wing structure applications. The aluminum product has a minimum yield strength of [75 ksi?0.8×(thickness in inch?3.94 inch)] in LT direction and [76 ksi?0.8×(thickness in inch?3.94 inch)] in L direction for more than 2 inch thick product in T7651 temper. Besides strength, product provides necessary damage tolerance performance as well as corrosion resistance performance suitable for aerospace application.Type: ApplicationFiled: April 22, 2013Publication date: August 27, 2015Inventors: Ralph Dorward, Paul John Ainsworth, Florence A. Baldwin, Philippe Lassince, Zhengdong Long, Robert A. Matuska, Roy Austin Nash, Raymond D. Parkinson, Timothy Allen Taylor
-
Publication number: 20060151075Abstract: The present invention relates to a method for producing Al—Zn—Cu—Mg type alloy plates comprising between 4 and 12% zinc, less than 4% magnesium and less than 4% copper, other elements?0.5% each, and the remainder aluminum. The method comprising hot rolling, solution heat-treatment, quenching, controlled stretching with permanent elongation greater than 0.5% and aging, wherein the elapsed time D between the end of quenching and the start of controlled stretching is less than 2 hours. The invention further relates to plates and products produced or capable of being produced using such methods.Type: ApplicationFiled: December 13, 2005Publication date: July 13, 2006Inventors: Sjoerd Van Der Veen, Fabrice Heymes, Julien Boselli, Philippe Lequeu, Philippe Lassince
-
Patent number: 6692589Abstract: A process for forming a structure element, particularly an lower wing element of an aircraft, manufactured from a rolled, extruded or forged product made of an alloy of composition (% by weight) Cu=4.6-5.3, Mg=0.10-0.50, Mn=0.15-0.45, Si<0.10, Fe<0.15, Zn<0.20, Cr<0.10, other elements <0.05 each and <0.15 total, remainder Al. The product is treated by solution heat treating, quenching, controlled tension to more than 1.5% permanent deformation and aging.Type: GrantFiled: April 24, 2003Date of Patent: February 17, 2004Assignee: Pechiney RhenaluInventors: Timothy Warner, Philippe Lassince, Philippe Lequeu
-
Publication number: 20030217793Abstract: Rolled, extruded or forged product made of an AlCuMg alloy processed by solution heat treatment, quenching and cold stretching, to be used in the manufacture of aircraft structural elements, with the following composition (% by weight):Type: ApplicationFiled: June 19, 2003Publication date: November 27, 2003Applicant: PECHINEY RHENALUInventors: Timothy Warner, Philippe Lassince, Philippe Lequeu
-
Publication number: 20030207141Abstract: The purpose of the invention is a structure element, particularly an lower wing element of an aircraft, manufactured from a rolled, extruded or forged product made of an alloy with composition (% by weight):Type: ApplicationFiled: April 24, 2003Publication date: November 6, 2003Applicant: PECHINEY RHENALUInventors: Timothy Warner, Philippe Lassince, Philippe Lequeu
-
Patent number: 6602361Abstract: Rolled product for use in the manufacture of aircraft structural elements, made of an AlCuMg alloy processed by solution heat treatment, quenching and cold stretching. The product has a composition consisting essentially of, in % by weight: Fe<0.15; Si<0.15; Cu:3.8-4.4; Mg:1-1.5; Mn:0.5-0.8; Zr:0.08-0.15; other elements: <0.05 each and <0.15 total. This product has a thickness of between 6 and 60 mm, with an ultimate tensile strength Rm(L) in the quenched and stretched temper >475 MPa and yield stress R0.2(L)>370 MPa, with a ratio Rm(L)/R0.2(L)>1.25.Type: GrantFiled: January 10, 2000Date of Patent: August 5, 2003Assignee: Pechiney RhenaluInventors: Timothy Warner, Philippe Lassince, Philippe Lequeu
-
Patent number: 6569542Abstract: The purpose of the invention is a structure element, particularly an lower wing element of an aircraft, manufactured from a rolled, extruded or forged product made of an alloy with composition (% by weight): Cu=4.6-5.3, Mg=0.10-0.50, Mn=0.15-0.45, Si <0.10, Fe<0.15, Zn<0.20, Cr<0.10, other elements <0.05 each and <0.15 total, the remainder being Al treated by solution heat treating, quenching, controlled tension to more than 1.5% permanent deformation and aging.Type: GrantFiled: December 13, 2000Date of Patent: May 27, 2003Assignee: Pechiney RhenaluInventors: Timothy Warner, Philippe Lassince, Philippe Lequeu
-
Patent number: 6528183Abstract: Clad sheet made up of a core sheet and a cladding layer on one or two core sheet surfaces. The core sheet is formed of an alloy having the composition (% by weight) Si: 0.7-1.3, Mg: 0.6-1.2, Cu: 0.5-1.1, Mn: 0.15-1.0, Zn<0.5, Fe<0.5, Zr<0.2, Cr<0.25, other elements <0.05 each and <0.15 total, the remainder aluminum. The cladding is formed of an AlZn alloy having a thickness of between 1 and 15% of the clad sheet thickness, having the composition (% by weight) Zn: 0.25-0.7, Fe<0.40, Si<0.40, Cu, Mn, Mg, V or Ti <0.10, other elements <0.05 each and 0.15 total.Type: GrantFiled: July 5, 2001Date of Patent: March 4, 2003Assignee: Pechiney RhenaluInventors: Ronan Dif, Bernard Bes, Philippe Lassince, Herve Ribes
-
Publication number: 20020031682Abstract: The object of the invention is a sheet clad on one or both sides, formed of a core sheet in an alloy having the composition (% by weight):Type: ApplicationFiled: July 5, 2001Publication date: March 14, 2002Inventors: Ronan Dif, Bernard Bes, Philippe Lassince, Herve Ribes
-
Publication number: 20020014288Abstract: Rolled, extruded or forged product made of an AlCuMg alloy processed by solution heat treatment, quenching and cold stretching, to be used in the manufacture of aircraft structural elements, with the following composition (% by weight): 1 Fe<0.15 Si<0.15 Cu:3.8-4.4 Mg:1-1.5 Mn:0.5-0.8 Zr:0.08-0.Type: ApplicationFiled: January 10, 2000Publication date: February 7, 2002Inventors: TIMOTHY WARNER, PHILIPPE LASSINCE, PHILIPPE LEQUEU
-
Publication number: 20010006082Abstract: The purpose of the invention is a structure element, particularly an lower wing element of an aircraft, manufactured from a rolled, extruded or forged product made of an alloy with composition (% by weight): Cu=4.6-5.3, Mg=0.10-0.50, Mn=0.15-0.45, Si <0.10, Fe<0.15, Zn<0.20, Cr<0.10, other elements <0.05 each and <0.15 total, the remainder being Al treated by solution heat treating, quenching, controlled tension to more than 1.5% permanent deformation and aging.Type: ApplicationFiled: December 13, 2000Publication date: July 5, 2001Inventors: Timothy Warner, Philippe Lassince, Philippe Lequeu