Abstract: A method of fabricating a composite nozzle for water-cooled, high temperature gas turbines is provided wherein the nozzle comprises a thermally conducting copper core, a top endwall, a bottom endwall, metal tubing through which water may pass embedded in and extending through the core and into the endwalls and a preformed cladding to protect the nozzle against corrosion. The method utilizes hot isostatic pressure to diffusion bond the nozzle components into an assembly and bond the corrosion resistant cladding to the outer surface of the assembly.

Abstract: A method for forming a liquid cooled airfoil for a gas turbine is disclosed. A plurality of holes are formed at spaced locations in an oversized airfoil blank. A pre-formed composite liquid coolant tube is bonded into each of the holes. The composite tube includes an inner member formed of an anti-corrosive material and an outer member formed of a material exhibiting a high degree of thermal conductivity. After the coolant tubes have been bonded to the airfoil blank, the airfoil blank is machined to a desired shape, such that a portion of the outer member of each of the composite tubes is contiguous with the outer surface of the machined airfoil blank. Finally, an external skin is bonded to the exposed outer surface of both the machined airfoil blank and the composite tubes.