Abstract: Systems and methods for preparing enriched biological samples, and methods of use thereof are described herein. The systems can include a containment device connected to a first insert to collect tissue fragments in the containment device or to a second insert to incubate tissue fragments with a blood sample in the containment device. The methods can include methods for preparing a cytokine or growth factor-enriched biological sample, such as IL-1 Ra-enriched serum, methods of treating inflammation, inflammatory joint, or rheumatoid arthritis, and methods of preventing inflammation of a joint following arthroscopic surgery.

Abstract: The present invention is directed to a 6xxx series aluminum alloy composition, comprising, consisting essentially of, or consisting of (by weight %) of 0.5-1.5% Si, 0.1-0.7% Cu, 0.5-1.5% Mg, 0.3-1.2% Zn, 0.05-0.35% Cr and allowable impurities of 0.8% Fe, 0.8% Mn, 0.15% Zr, 0.15% Ti, with other elements restricted as unavoidable impurities limited to 0.05% each and 0.15% total with the balance being aluminum. This 6xxx series aluminum alloy is capable of being produced with high amounts of post-consumer recycled material which significantly reduces environmental impact from producing this material, while still meeting and in most cases exceeding material attribute requirements for general engineering applications.

Abstract: Dispersoids 7xxx aluminum alloy products with enhanced fatigue crack growth deviation and Environmentally Assisted Cracking (EAC) resistance are disclosed. The 7xxx aluminum alloy comprises 1 to 3 wt. % Cu, 1.2 to 3 wt. % Mg, 4 to 8.5 wt. % Zn, up to 0.3 wt. % Mn, up to 0.15 wt. % Zr, up to 0.3 wt. % Cr dispersoid elements, incidental elements, and the balance Al. In one embodiment, the alloy includes Zr + Cr + Mn in the range of 0.2 to 0.8 wt. %. In another embodiment, the alloy includes Zr + Mn in the range of 0.07 to 0.7 wt. %. This alloy can be fabricated to plate, extrusion, or forging products, and is especially suitable for aerospace structural components. The products have enhanced EAC resistance and fatigue crack growth deviation resistance. Meanwhile, the products have an excellent combination of strength, fracture toughness, ductility at different orientations, and Stress Crack Corrosion (SCC), and exfoliation corrosion resistance suitable for aerospace application.

Abstract: The present invention is directed to a 7xxx series aluminum alloy composition comprising, consisting essentially of, or consisting of (by weight %) of 1.0-1.8% Mg; 7.0-8.3% Zn; 0.10-0.25% Zr; with up to 0.80% Cu and allowable impurities of 0.3% Si, 0.4% Fe, 0.4% Mn, and 0.1% Ti, with other elements restricted as unavoidable impurities limited to 0.05% each and 0.15% total and MgZn2 range of 7.0-9.9% with the balance being aluminum. This 7xxx series aluminum alloy is capable of being produced to achieve its maximum strength by quenching from an elevated hot working operation, such as extrusion, forging or rolling. In one embodiment the alloy is capable of meeting strength levels in excess of 65 KSI/450 MPa yield tensile strength, 69 KSI/480 MPa ultimate tensile strength and 11% elongation.

Abstract: The present invention relates to an aluminum 6XXX (Al—Mg—Si) alloy extrusion component exhibiting a superior combination of strength and energy absorption for crash management applications in automotive markets and for other applications where energy absorption is a critical property. These components provide yield strengths greater than 260 MPa, and preferably greater than 280 MPa, while simultaneously providing energy absorption per unit cross-sectional area of greater than 20 kJ/mm2 using the defined crush testing parameters in the present specification.

Abstract: A substantially Pb-free aluminum alloy consisting essentially of (in weight percent) Si<0.40; Fe<0.70; Cu 5.0-6.0; Zn<0.30; Bi 0.20-0.80; Sn 0.10-0.50 with the remainder being aluminum and incidental impurities. In one embodiment for applications that are sensitive to cracking from stresses generated during machining, the Bi/Sn ratio (in terms of weight percent) is less than 1.32/1 and producing in a T8 temper. On another embodiment for applications that are not sensitive to cracking from stresses during machining but would benefit from smaller machine chip size and more aggressive material removal rates, the aluminum alloy is produced using a T6 temper. The substantially Pb-free aluminum alloy has mechanical properties that include Ultimate Tensile Strength ?45.0 KSI/311 MPa, Yield Strength ?38.0 KSI/262 MPa, and % Elongation ?10%.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A substantially Pb-free aluminum alloy consisting essentially of (in weight percent) Si<0.40; Fe<0.70; Cu 5.0-6.0; Zn<0.30; Bi 0.20-0.80; Sn 0.10-0.50 with the remainder being aluminum and incidental impurities. In one embodiment for applications that are sensitive to cracking from stresses generated during machining, the Bi/Sn ratio (in terms of weight percent) is less than 1.32/1 and producing in a T8 temper. On another embodiment for applications that are not sensitive to cracking from stresses during machining but would benefit from smaller machine chip size and more aggressive material removal rates, the aluminum alloy is produced using a T6 temper. The substantially Pb-free aluminum alloy has mechanical properties that include Ultimate Tensile Strength ?45.0 KSI/311 MPa, Yield Strength ?38.0 KSI/262 MPa, and % Elongation ?10%.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The homogenization cycle of an alloy is optimized and controlled by defining a target degree of transformation to achieve at least one metallurgical property for an alloy. The desired metallurgical properties include, but are not limited to, dissolving precipitation hardening phases, transforming insoluble phases into preferred phases and precipitating the dispersoid phases to the proper size and distribution. Using regression analysis, a transformation model is obtained to predict the degree of transformation of an alloy by analyzing the degree of transformation of a plurality of sample alloys subjected to heating at predetermine temperatures for predetermined amounts of time.