Abstract: A niobium-silicide refractory metal intermetallic composite having enhanced material characteristics, such as oxidation resistance, creep resistance, and toughness, and turbine components made therefrom.

Abstract: A turbine combustion system comprises at least one turbine combustion component that is provided with a protective coating on the outer surface otherwise known as the non-flame surface of at least one turbine combustion component. The at least one turbine combustion component comprises an inner surface that defines a hot flame path area and an outer surface. The coating on the outer surface of the combustion components provides protection for the components from at least one of oxidation, nitridation, and hot corrosion.

Abstract: A method of forming an internal channel within an article, such as a cooling channel in an air-cooled blade, vane, shroud, combustor or duct of a gas turbine engine. The method generally entails forming a substrate to have a groove recessed in its surface. A sacrificial material is then deposited in the groove to form a filler that can be preferentially removed from the groove. A permanent layer is then deposited on the surface of the substrate and over the filler, after which the filler is removed from the groove to yield the desired channel in the substrate beneath the permanent layer.

Abstract: A coating for use on a superalloy substrate comprising a diffusion barrier as an intermediate layer overlying the substrate and underlying a protective coating having a high aluminum content. The diffusion barrier layer is characterized by having low solubility for aluminum from either the substrate or the protective coating. Further, the diffusion barrier layer has low interdiffusivity for elements from the substrate and the coating, a minimal impact on the mechanical properties of the article which is coated, a minimal thermal expansion mismatch with both the substrate and the high aluminum content protective coating, and can be applied readily using existing coating application techniques. The diffusion barrier is preferably a single phase alloy or intermetallic compound.

Abstract: A continuously-graded bond coat comprises a gradient of at least one material characteristic value. The gradient extends from a first material characteristic value at a first surface region to a second material characteristic value at a second surface region. The continuously-graded bond coat can be used in a thermal barrier coating system. A source ingot for forming the continuously-graded bond coat comprises aluminum, in an atomic percent range from about 50.0 to less than about 100.0; chromium in an atomic percent range from about 5.0 to about 40.0; silicon in an atomic percent range from about 1.0 to about 17.0; zirconium in an atomic percent range from about a trace to about a 0.5, yttrium in an atomic percent range from a trace to about 2.0; and hafnium in an atomic percent range from about 0.5 to about 2.0. A method for forming the continuously-graded bond coat with the gradient is also provided by the invention.

Abstract: A liquid metal cooled directional solidification process provides improved solidification characteristics at the solidification front. In the process, a mold is filled with molten metal; and a solidification interface is caused to pass through the molten metal by progressively immersing the mold into a cooling liquid. The cooling liquid is a eutectic or near eutectic metal composition. A directional solidification furnace includes a heating furnace, a liquid cooling bath and a mold positioner. The heating furnace has an open bottom end through which a heated mold containing molten metal is lowered from the furnace. The liquid cooling bath comprises a molten eutectic or near eutectic metal composition positioned beneath the open end of the furnace. The mold positioner gradually lowers the heated mold from the furnace, through the open end and immerses the mold into the liquid cooling bath.

Abstract: A method of forming an internal channel within an article, such as a cooling channel in an air-cooled blade, vane, shroud, combustor or duct of a gas turbine engine. The method generally entails forming a substrate to have a groove recessed in its surface. A sacrificial material is then deposited in the groove to form a filler that can be preferentially removed from the groove. A permanent layer is then deposited on the surface of the substrate and over the filler, after which the filler is removed from the groove to yield the desired channel in the substrate beneath the permanent layer.

Abstract: A cast superalloy article having a unidirectional crystal structure that is substantially defect free with primary dendrite arm spacing greater than 150 &mgr;m is provided. The unidirectional crystalline microstructure comprises a longitudinal columnar structure aligned parallel with the direction of solidification where said columnar structure is a single crystal or polycrystals or mixtures thereof.

Abstract: A nickel-base gamma-sigma intermetallic matrix composite material suitable for forming gas turbine engine components and structural coatings for such components. The composite material contains, in weight percent, about 20 to 50 chromium, about 0 to 32 molybdenum, and about 0.5 to 7 silicon, with the balance being nickel and incidental impurities. In addition, the composite material may contain aluminum and titanium in amounts of up to about 7 and 3 weight percent, respectively. The resulting intermetallic matrix composite material is characterized by a sigma volume fraction of greater than 30 percent, preferably at least about 50 percent, and may have a dendritic, fibrous or lamellar microstructure. The composite material can be cast to form a component, or deposited by known techniques to form a structural coating on a component.