Method for preparing pre-coated, metallic components and components prepared thereby
AssigneeThe Boeing Company
InventorSteven Keener
Life of this patent
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Abstract
A high-strength, corrosion- and heat-resistant aircraft structural component such as a fastener is prepared by providing a corrosion-resistant stainless steel or heat-resistant superalloy metallic component precursor that is not in its final heat-treated state, and coating with an aluminum-containing, curable polyaromatic phenolic coating material having a non-volatile portion that is predominantly organic and is curable at about the high-strength metallic alloy component's stress equalizing tempering temperature. The coated, high-strength metallic-alloy component is then thermally treated to concurrently impart pre-determined metallurgical properties to the finished, metallic substrate, and cure the organic, aluminum-containing coating.
Claims25
1-22. (canceled)
A stress equalized high-strength, corrosion-resistant aircraft structural alloy component comprising a coating made from an organic, polyaromatic phenolic resin mixed with at least one plasticizer and an inorganic additive selected from the group consisting of aluminum powder and chromate filler.
A stress equalized high-strength, corrosion-resistant aircraft structural stainless steel alloy component comprising a coating made from an organic, polyaromatic phenolic resin mixed with at least one plasticizer and an inorganic additive selected from the group consisting of aluminum powder and chromate filler.
A high-strength, aircraft structural alloy component prepared according to the method of claim 1.
A high-strength, aircraft structural nickel-base alloy component prepared according to the method of claim 12.
39-47. (canceled)
An aircraft comprising an alloy aircraft structural component comprising:
- an alloy precursor having a pre-determined stress equalizing heat-treatment temperature, said precursor selected from the group consisting of 302, 303, 304, 305, 410, 416, 430, Custom 450, and 17-4PH stainless steels, said stainless steels having a pre-determined heat-treatment temperature;
- and
- a curable, organic coating comprising a polyaromatic phenolic resin mixed with at least one plasticizer, polytetrafluoroethylene and an inorganic additive selected from the group consisting of aluminum powder and chromate filler, said coating material having a non-volatile portion that is curable at about the pre-determined alloy stress equalizing heat-treatment temperature, said coating cured at a temperature sufficient to substantially concurrently cure the coating and heat-treat the alloy precursor.
An aircraft comprising an alloy aircraft structural component comprising:
- an alloy precursor having a pre-determined stress equalizing heat-treatment temperature, said precursor wherein the alloy precursor is selected from the group consisting of Monel 400, Monel K-500, Inconel 600, Inconel-X750, and A-286, said alloy precursor having a pre-determined heat-treatment temperature;
- and
- a curable, organic coating comprising a polyaromatic phenolic resin mixed with at least one plasticizer, polytetrafluoroethylene and an inorganic additive selected from the group consisting of aluminum powder and chromate filler, said coating material having a non-volatile portion that is curable at about the pre-determined alloy stress equalizing heat-treatment temperature, said coating cured at a temperature sufficient to substantially concurrently cure the coating and heat-treat the alloy precursor.
An aircraft comprising an alloy aircraft structural component comprising:
- an alloy precursor having a pre-determined stress equalizing heat-treatment temperature, said precursor wherein the alloy precursor is A-286, said alloy precursor having a pre-determined heat-treatment temperature;
- and
- a curable, organic coating comprising a polyaromatic phenolic resin mixed with at least one plasticizer, polytetrafluoroethylene and an inorganic additive selected from the group consisting of aluminum powder and chromate filler, said coating material having a non-volatile portion that is curable at about the pre-determined alloy stress equalizing heat-treatment temperature, said coating cured at a temperature sufficient to substantially concurrently cure the coating and heat-treat the alloy precursor.
Dependencies are inferred from the claim text.