초록 ▼

The disclosed composite airfoil includes a three-dimensional composite core extending longitudinally and having a chord-wise direction. The core has a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal dire

The disclosed composite airfoil includes a three-dimensional composite core extending longitudinally and having a chord-wise direction. The core has a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions. A composite skin covers the opposing sides and has an exterior surface providing an airfoil contour. The skin includes a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface. A sum of the core in-plane and total skin in-plane thicknesses at a central portion of the composite airfoil is a total in-plane thickness. The total skin in-plane thickness at the central portion is less than 50% of the total in-plane thickness.

대표청구항 ▼

1. A composite airfoil comprising: a three-dimensional composite core extending longitudinally and having a chord-wise direction, having a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions;a com

1. A composite airfoil comprising: a three-dimensional composite core extending longitudinally and having a chord-wise direction, having a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions;a composite skin covering the opposing sides and having an exterior surface providing an airfoil contour, the skin having a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface, a sum of the core in-plane and skin in-plane thicknesses at a central portion of the composite airfoil being a total in-plane thickness, with the total skin in-plane thickness at the central portion being between 25% to 35% of the total in-plane thickness; andwherein the total skin in-plane thickness is 10% of the total in-plane thickness over a root from which the airfoil longitudinally extends. 2. The composite airfoil according to claim 1, wherein the composite skin comprises multiple woven fiber plies wrapped about the composite core, which is constructed from a fibrous preform, the composite core and composite skin bound together by a resin. 3. The composite airfoil according to claim 1, wherein the total skin in-plane thickness is approximately 30% of the total in-plane thickness. 4. The composite airfoil according to claim 3, wherein the skin in-plane thicknesses are each approximately 15%. 5. The composite airfoil according to claim 1, wherein the skin in-plane thicknesses are approximately equal to one another. 6. A composite airfoil comprising: a three-dimensional composite core extending longitudinally and having a chord-wise direction, having a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions;a composite skin covering the opposing sides and having an exterior surface providing an airfoil contour, the skin having a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface, a sum of the core in-plane and skin in-plane thicknesses at a central portion of the composite airfoil being a total in-plane thickness, with the total skin in-plane thickness at the central portion being less than 50% of the total in-plane thickness; andwherein the composite core includes a recess near a leading edge of the airfoil, and a reinforcement secured over the recess with the composite skin arranged between and directly interconnecting the reinforcement and composite core; andwherein the total skin in-plane thickness is 10% of the total in-plane thickness over a root from which the airfoil longitudinally extends. 7. The composite airfoil according to claim 6, wherein the reinforcement extends longitudinally from a tip toward the root and in the chord-wise direction over the tip and longitudinally along a trailing edge portion of the airfoil. 8. The composite airfoil according to claim 7, wherein the total skin in-plane thickness is substantially constant along 80% of the radial distance outward from the root. 9. A composite airfoil comprising: a three-dimensional composite core extending longitudinally and having a chord-wise direction, having a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions;a composite skin covering the opposing sides and having an exterior surface providing an airfoil contour, the skin having a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface, a sum of the core in-plane and skin in-plane thicknesses at a central portion of the composite airfoil being a total in-plane thickness, with the total skin in-plane thickness at the central portion being less than 50% of the total in-plane thickness; andwherein the composite core and composite skin provide at least a portion of the airfoil and a root from which the airfoil longitudinally extends; andwherein the total skin in-plane thickness is substantially constant along 80% of the radial distance outward from the root. 10. A method of manufacturing a composite airfoil comprising: providing a fibrous preform core;covering the fibrous preform core in at least one dry woven layer to provide a skin;inserting the covered fibrous preform core in a mold cavity; andimpregnating the covered fibrous preform core with resin to produce the composite airfoil wherein a total skin thickness is less than a core thickness at a central portion of the composite airfoil, wherein the total skin thickness is between 25% to 35% of the total thickness of the airfoil at the central portion; andwherein a total skin in-plane thickness is 10% of a total in-plane thickness over a root from which the airfoil longitudinally extends. 11. The method according to claim 10, wherein the total skin thickness is approximately 30% of the total thickness of the airfoil at the central portion. 12. The method according to claim 11, wherein the skin thickness on each of opposing sides of the airfoil at the central portion is approximately 15%. 13. The method according to claim 10, wherein the skin thickness on each of opposing sides of the airfoil at the central portion are approximately equal to one another.