Method of manufacturing a hybrid turbine rotor

A method for fabricating a hybrid dual property turbine engine wheel assembly comprising:

• preforming a bladed ring with airfoil blades having an exact dimensional control therebetween to maintain aerodynamic flow paths through the ring and with a base rim thereon from a cast, corrosion and thermally resistant superalloy material, said base rim having a premachined close tolerance ID and a front side and a rear side, preforming a disc of consolidated powdered metal having a controlled OD, press fitting the bladed ring to the disc to form a near line-to-line interface therebetween with continuously circumferentially formed front and rear joint lines and with continuous contact across the full facing surface areas of both the base rim ID and the controlled OD of the disc from the front side to the rear side of the base rim ID thereby to prevent collapse of the interface and resultant loss of dimensional control between adjacent airfoils during a subsequent hot isostatic pressing of the joined bladed ring and disc, sealing the full extent of the joint lines with high melt temperature sealant to maintain a clean press fit at the interface between the outside diameter of the disc and the inside diameter of the bladed ring element and a sealed, pressure tight interface, and to define an exposed exterior planar extent on the bladed metal ring and the disc for receiving direct application of hot isostatic fluid without flow of such fluid into the interface, and thereafter hot isostatically pressing the joined bladed ring and disc by direct fluid pressure across the full exterior planar extent of the joined parts to form a diffused metallurgical bond between the base rim and the disc.

A method for fabricating a hybrid dual property turbine engine wheel assembly comprising:

• preforming a bladed ring with airfoil blades having an exact dimensional control therebetween to maintain aerodynamic flow paths through the ring and with a base rim thereon from a cast, corrosion and thermally resistant superalloy material, said base rim having a premachined close tolerance ID and a front side and a rear side, preforming a disc of consolidated powdered metal having a controlled OD, press fitting the bladed ring to the disc to form a near line-to-line interface therebetween with continuously circumferentially formed front and rear joint lines and with continuous contact across the full facing surface areas of both the base rim ID and the controlled OD of the disc from the front side to the rear side of the base rim ID thereby to prevent collapse of the interface and resultant loss of dimensional control between adjacent airfoils during a subsequent hot isostatic pressing of the joined bladed ring and disc, sealing the full extent of the joint lines with high melt temperature sealant to maintain a clean press fit at the interface between the outside diameter of the disc and the inside diameter of the bladed ring element and a sealed, pressure tight interface, said high melt temperature sealant being a boronsilicon modified braze powder, said braze powder being applied to cover the joint lines and thereafter held under vacuum while being heated to a temperature of 2225.degree. F. for melting the powder to cover the joint lines, thereafter reducing the braze temperature to solidify the braze material and then increasing the braze temperature and maintaining it to permit diffusion of boron and silicon constituents into the parent material of the disc and bladed ring to elevate the remelt temperature of the sealant, and to define an exposed exterior planar extent on the bladed metal ring and the disc for receiving direct application of hot isostatic fluid without flow of such fluid into the interface, and thereafter hot isostatically pressing the joined bladed ring and disc by direct fluid pressure across the full exterior planar extent of the joined parts to form a diffused metallurgical bond between the base rim and the disc.

A method for fabricating a hybrid, dual property wheel assembly comprising the steps of preforming a plurality of blade elements of a first predetermined highly solidified alloy material having a base, fixturing said blade elements into a bladed ring and tack welding each of the blades together in the ring at an interface between each of the blades, vacuum seal brazing each of the exposed joint areas between the tack welded blades, hot isostatically pressing the assembly to achieve diffusion bonding across the interface at each of the vacuum braze sealed joint areas, thereafter machining the inside diameter of the bladed ring, preforming a powdered metal disc with controlled OD, shrink fitting the bladed ring to the outer diameter of the powder metal disc to form a front and rear face joint line, sealing the front and rear face joint lines with a high melt temperature sealant, said high melt temperature sealant being a boron-silicon modified braze powder, said braze powder being applied to cover the joint lines and thereafter held under vacuum while being heated to a temperature of 2225.degree. F. for melting the powder to cover the joint lines, thereafter reducing the braze temperature to solidify the braze material and then increasing the braze temperature and maintaining it to permit diffusion of boron and silicon constituents into the parent material of the disc and bladed ring to elevate the remelt temperature of the sealant, and thereafter hot isostatically pressing the joined bladed ring and disc to produce a diffusion bond between the bladed ring and the disc.