Intermetallic Composite Formation and Fabrication from Nitride-Metal Reactions

Abstract

In a method of making a molybdenum, molybdenum silicide and molybdenum silicon boride composite material, a boron nitride powder, a silicon nitride powder and a molybdenum powder are mixed to form a composite precursor. The composite precursor is sintered in an atmosphere consisting essentially of hydrogen and argon to form a sintered material. The sintered material is hot isostatic pressed to form the composite material into a final shape.

Description

CROSS-REFERENCE TO RELATED APPLICATION(S)[0001]This application claims the benefit of U.S. Provisional Patent Application Ser. No. 60 / 947,503, filed Jul. 2, 2007, the entirety of which is hereby incorporated herein by reference.STATEMENT OF GOVERNMENT INTEREST[0002]This invention was made with support from the U.S. government under grant number NAVAIR N00421-041-0002, awarded by the Office of Naval Research. The government may have certain rights in the invention.BACKGROUND OF THE INVENTION[0003]1. Field of the Invention[0004]The present invention relates to composite materials and, more specifically, to a composite material including molybdenum, molybdenum silicides and molybdenum silicon boride.[0005]2. Description of the Prior Art[0006]Nickel super alloy turbine blades in modern jet engines operate at temperatures approaching 1150° C. Using technologies such as thermal barrier coatings and elaborate cooling schemes, such engine temperatures may be pushed as high as 1500° C. Drama...

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Benefits of technology

[0015]In another aspect, the invention is a composite material having an outer surface and including a metallic phase continuous molybdenum matrix, a molybdenum silicide intermetallic phase, a molybdenum silicon boride intermetallic phase and a borosilicate glass layer. The metallic phase continuous molybdenum matrix has an average grain size of less than 4.0 microns. The molybdenum s

Problems solved by technology

Nickel super alloy turbine blades in modern jet engines operate at temperatures approaching 1150° C. Using technologies such as thermal barrier coatings and elaborate cooling schemes, such engine temperatures may be pushed as high as 1500° C. Dramatic increases in the performance of such engines can be gained by operating at higher temperatures, but as more elaborate systems are employed to cool the airfoils, engine efficiency is reduced.

Refractory metals such as molybdenum have high melting points and excellent high temperature mechanical properties; however, the oxidation resistance of these metals is typically poor.

Unfortunately, existing composites employing these phases have grain structu

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