Heat treatment of additively manufactured aluminum alloy
AssigneeThe Boeing Company
InventorsPaul N. Wilson, Michael R. Zolnowski, Russell W. Cochran, Burke L. Reichlinger
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Abstract
A method for heat treating an additively manufactured A205 aluminum alloy component (“AM205 component”) to produce a uniform grain distribution within the AM205 component is disclosed. The method includes solution aging the AM205 component at a first temperature for a first time period, wherein the first time period is less than five hours and overaging the AM205 component after the solution aging.
Claims29
A method of heat treating an A205 aluminum alloy component additively manufactured from aluminum alloy powder, the method comprising:
- solution aging the A205 aluminum alloy component additively manufactured from aluminum alloy powder at a first temperature of 400 to 700 degrees Celsius for a first time period, wherein the first time period is between three hours and 45 minutes and four hours and 15 minutes;
- overaging the aluminum alloy component at a second temperature lower than the first temperature after the solution aging;
- and
- between the solution aging and the overaging, lowering a temperature of the A205 aluminum alloy component to a temperature below the second temperature;
- wherein the heat treating increases both a 0.2% yield stress and an ultimate tensile strength of the aluminum alloy component.
A method for heat treating an additively manufactured A205 aluminum alloy component, the method comprising:
- solution aging the A205 aluminum alloy component at 540 degrees Celsius for a first time period, wherein the first time period is between three hours and 45 minutes and four hours and 15 minutes;
- overaging the aluminum alloy component at a second temperature lower than the first temperature after the solution aging;
- and
- between the solution aging and the overaging, lowering a temperature of the A205 aluminum alloy component to a temperature below the second temperature;
- wherein the heat treating increases a 0.2% yield stress of the aluminum alloy component to a value greater than 48 ksi, and increases an ultimate tensile strength of the aluminum alloy component to a value greater than 62 ksi.
Dependencies are inferred from the claim text.