Abstract: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing blade conical surface; an airfoil component, wherein the at least one airfoil component has been created from a single, unitary piece of material and further includes a plurality of individual airfoil blades and a continuous radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

Abstract: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing blade conical surface; an airfoil component, wherein the at least one airfoil component has been created from a single, unitary piece of material and further includes a plurality of individual airfoil blades and a continuous radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

Abstract: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing blade conical surface; an airfoil component, wherein the at least one airfoil component has been created from a single, unitary piece of material and further includes a plurality of individual airfoil blades and a continuous radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

Abstract: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing conical surface; an airfoil component, wherein the airfoil component further includes a plurality of individual airfoil blades, wherein at least a portion of each individual airfoil blade has been reinforced with at least one metal matrix composite, and wherein each of the plurality of airfoil blades further includes a radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

Abstract: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a plurality of radially outwardly facing blade conical surfaces; an airfoil component, wherein the airfoil component further includes: a plurality of individual airfoil blades, wherein each of the plurality of airfoil blades further includes a radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

Abstract: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a plurality of radially outwardly facing blade conical surfaces; an airfoil component, wherein the airfoil component further includes: a plurality of individual airfoil blades, wherein each of the plurality of airfoil blades further includes a radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

Abstract: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing blade conical surface; an airfoil component, wherein the at least one airfoil component has been created from a single, unitary piece of material and further includes a plurality of individual airfoil blades and a continuous radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

Abstract: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing conical surface; an airfoil component, wherein the airfoil component further includes a plurality of individual airfoil blades, wherein at least a portion of each individual airfoil blade has been reinforced with at least one metal matrix composite, and wherein each of the plurality of airfoil blades further includes a radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

Abstract: A method for repairing a discrete damaged portion of an article surface, for example of a laminated composite material, includes applying an uncured repair material at the damaged portion and then subjecting the repair material and the discrete damaged portion to a vacuum to remove air entrapped in the repair material and the discrete damaged portion. One form of the invention uses a vacuum tool comprising an outer wall including an opening there through having a peripheral edge shaped to conform generally with a portion of the article surface about the damaged portion, and gas evacuation means. The tool is combined with a releasable gas seal generally shaped to interface between the peripheral edge and the article surface and release from the article surface.

Abstract: Increased impact resistance capability is achieved in a cost and weight efficient manner by providing a spinner made of a 3-D orthogonal woven composite material. The spinner defines a generally conical shell having a plurality of axial rib stiffeners and at least one circumferential rib stiffener integrally formed thereon. The combination of the integral rib stiffeners with the 3-D orthogonal woven composite material results in a substantially greater torsional stiffness. The use of the 3-D orthogonal woven composite material also eliminates delamination found in laminated composite spinners.

Abstract: A rotator member, for example an airfoil of a rotating blade, is provided with additional stiffness in a radially outer portion of the member by including in the outer portion at least one corrugation extending generally along the width, for example chordwise, of the member.

Abstract: A method for repairing a discrete damaged portion of an article surface, for example of a laminated composite material, includes applying an uncured repair material at the damaged portion and then subjecting the repair material and the discrete damaged portion to a vacuum to remove air entrapped in the repair material and the discrete damaged portion. One form of the invention uses a vacuum tool comprising an outer wall including an opening there through having a peripheral edge shaped to conform generally with a portion of the article surface about the damaged portion, and gas evacuation means. The tool is combined with a releasable gas seal generally shaped to interface between the peripheral edge and the article surface and release from the article surface.

Abstract: A rotor blade pair for rotation around an axial centerline is provided which includes a platform, a first and a second airfoil, and a root having a first and second wall. The platform has an inner and an outer radial surface. The first and second airfoils extend out from the outer radial surface of the platform. The root walls extend out from said inner radial surface of the platform, and are integrally connected to one another, forming a hollow between the walls and the inner radial surface. The first wall is substantially aligned with the first airfoil and the second wall is substantially aligned with the second airfoil.

Abstract: A turbine engine rotor assembly disk is provided which includes a forward web, an aft web, a plurality of first stub shafts, and a plurality of second stub shafts. The first and second stub shafts have axial ends and web ends. The stub shafts are attached to the respective forward or aft web, at the web end. The first and second stub shafts are equal in number, similarly spaced around the axial centerline, and attached to one another by fasteners.