초록 ▼

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 fu

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.

대표청구항 ▼

What is claimed is: 1. A system for manufacturing an integrally bladed rotor, comprising: (a) a ring component, wherein the ring component further includes: (i) at least one metal matrix composite; (ii) a plurality of radially outwardly facing blade conical surfaces; and (iii) a build-up region, wh

What is claimed is: 1. A system for manufacturing an integrally bladed rotor, comprising: (a) a ring component, wherein the ring component further includes: (i) at least one metal matrix composite; (ii) a plurality of radially outwardly facing blade conical surfaces; and (iii) a build-up region, wherein the build-up region is located along the plurality of radially outwardly facing blade conical surfaces of the outer diameter of the ring component; (b) an airfoil component, wherein the airfoil component further includes: (i) a plurality of individual airfoil blades; (ii) wherein at least an internal core portion of each individual airfoil blade has been reinforced with at least one metal matrix composite; (iii) wherein each of the plurality of airfoil blades further includes a radially inwardly facing blade conical surface; and (c) inertia welding means for frictionally engaging under an axially applied weld load the ring component and airfoil component to effect an inertia weld therebetween along the build-up region of the ring component and the inwardly facing blade conical surface of the airfoil component. 2. The system of claim 1, wherein the ring component of the integrally bladed rotor extends circumferentially and axially relative to the rotor's center of rotation, wherein at least one reinforcing fiber is included within the ring, and wherein the reinforcing fiber extends circumferentially in the direction of rotor rotation. 3. The system of claim 2, wherein the circumferentially oriented fiber is a single, continuous, fiber tow. 4. The system of claim 2, wherein the circumferentially oriented fiber includes a stack of multiple fiber layers oriented in a radial manner within the ring. 5. The system of claim 4, wherein the fiber layers include nano-size whisker fibers arranged randomly, circumferentially, or in layers. 6. The system of claim 1, wherein prior to application of the inertia welding means, each of the individual airfoil blades is machined to a predetermined shape for forming a complete circle around the ring component following the welding of the airfoil component to the ring component. 7. The system of claim 1, wherein following the welding of the airfoil component to the ring component, a quantity of material around the base of each airfoil blade is removed to a diameter smaller than the weld diameter between each conical surface. 8. The system of claim 1, wherein the angle of each conical surface is about 15°-75° relative to the rotor's centerline of rotation. 9. An integrally bladed rotor, comprising: (a) a ring component, wherein the ring component further includes: (i) at least one metal matrix composite; (ii) a plurality of radially outwardly facing blade conical surfaces; and (iii) a build-up region, wherein the build-up region is located along the plurality of radially outwardly facing blade conical surfaces of the outer diameter of the ring component; (b) an airfoil component, wherein the at least one airfoil component further includes: (i) a plurality of individual airfoil blades; (ii) wherein at least an internal core portion of each individual airfoil blade has been reinforced with at least one metal matrix composite; and (iii) wherein each of the plurality of airfoil blades further includes a radially inwardly facing blade conical surface; and (c) wherein the ring component and the airfoil component have been frictionally engaged with one another along the build-up region of the ring component and the inwardly facing blade conical surface of the airfoil component by inertia welding means under predetermined operating parameters. 10. The rotor of claim 9, wherein the ring component of the integrally bladed rotor extends circumferentially and axially relative to the rotor's center of rotation, wherein at least one reinforcing fiber is included within the ring, and wherein the reinforcing fiber extends circumferentially in the direction of rotor rotation. 11. The rotor of claim 10, wherein the circumferentially oriented fiber is a single, continuous, fiber tow. 12. The rotor of claim 10, wherein the circumferentially oriented fiber includes a stack of multiple fiber layers oriented in a radial manner within the ring. 13. The rotor of claim 12, wherein the fiber layers include nano-size whisker fibers arranged randomly, circumferentially, or in layers. 14. The rotor of claim 9, wherein prior to application of the inertia welding means, each of the individual airfoil blades is machined to a predetermined shape for forming a complete circle around the ring component following the welding of the airfoil component to the ring component. 15. The rotor of claim 9, wherein following the welding of the airfoil component to the ring component, a quantity of material around the base of each airfoil blade is removed to a diameter smaller than the weld diameter between each conical surface. 16. The rotor of claim 9, wherein the angle of each conical surface is about 15°-75° relative to the rotor's centerline of rotation. 17. A method for manufacturing an integrally bladed rotor, comprising: (a) providing a ring component, wherein the ring component further includes: (i) at least one metal matrix composite; (ii) a plurality of radially outwardly facing blade conical surfaces; and (iii) a build-up region, wherein the build-up region is located along the plurality of radially outwardly facing blade conical surfaces of the outer diameter of the ring component; (b) providing an airfoil component, wherein the airfoil component further includes: a plurality of individual airfoil blades; wherein at least an internal core 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 (c) using 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 build-up region of the ring component and the inwardly facing blade conical surface of the airfoil component. 18. The method of claim 17, further comprising forming each of the individual airfoil blades into a predetermined shape prior to the application of the inertia welding means so that the airfoil blades will form a complete circle around the ring component following the welding of the airfoil component to the ring component. 19. The method of claim 17, further comprising removing a quantity of material around the base of each airfoil blade following the welding of the airfoil component to the ring component to a diameter smaller than the weld diameter between each conical surface. 20. The method of claim 17, further comprising subjecting the assembled integrally bladed rotor to heat treatment sufficient to relieve internal stresses generated by inertia welding. 21. The method of claim 17, wherein the ring component of the integrally bladed rotor extends circumferentially and axially relative to the rotor's center of rotation, wherein at least one reinforcing fiber is included within the ring, and wherein the reinforcing fiber extends circumferentially in the direction of rotor rotation. 22. The method of claim 21, wherein the circumferentially oriented fiber further comprises at least one of a single, continuous, fiber tow and a group of randomly arranged nano-size whisker fibers. 23. The method of claim 21, wherein the circumferentially oriented fiber includes a stack of multiple fiber layers oriented in a radial manner within the ring. 24. The method of claim 23, wherein the fiber layers include nano-size whisker fibers arranged randomly, circumferentially, or in layers. 25. The method of claim 17, wherein the angle of each conical surface is about 15°-75° relative to the rotor's centerline of rotation.