초록 ▼

An airfoil comprises a leading edge, a trailing edge, and pressure and suction surfaces defined therebetween. An inner platform is coupled to a root section of the airfoil, with a curvilinear gusset extending along a lower surface of the inner platform, opposite the root section. An outer platform i

An airfoil comprises a leading edge, a trailing edge, and pressure and suction surfaces defined therebetween. An inner platform is coupled to a root section of the airfoil, with a curvilinear gusset extending along a lower surface of the inner platform, opposite the root section. An outer platform is coupled to a tip section of the airfoil, with a multi-lobed gusset extending along an upper surface of the inner platform, opposite the tip section.

대표청구항 ▼

1. An airfoil comprising: a leading edge, a trailing edge, and pressure and suction surfaces defined therebetween;an inner platform coupled to a root section of the airfoil, the inner platform comprising a curvilinear gusset extending along a lower surface of the inner platform, opposite the root se

1. An airfoil comprising: a leading edge, a trailing edge, and pressure and suction surfaces defined therebetween;an inner platform coupled to a root section of the airfoil, the inner platform comprising a curvilinear gusset extending along a lower surface of the inner platform, opposite the root section, wherein the curvilinear gusset extends along a camber line of the airfoil defined in the root section of the airfoil opposite the curvilinear gusset;an outer platform coupled to a tip section of the airfoil, the outer platform comprising a multi-lobed gusset extending along an upper surface of the outer platform, opposite the tip section;wherein the multi-lobed gusset comprises four legs meeting at a nexus, wherein two of the four legs extend axially forward from the nexus and two of the four legs extend axially aft from the nexus. 2. The airfoil of claim 1, wherein the curvilinear gusset comprises a web attached to the lower surface of the inner platform and a mounting element attached to the web, and further comprising an axially oriented bolt hole in the mounting element. 3. The airfoil of claim 2, wherein the inner platform comprises a radially oriented bolt hole. 4. The airfoil of claim 1, wherein the nexus is positioned opposite a maximum camber point on a camber line defined in the tip section of the airfoil, opposite the multi-lobed gusset. 5. The airfoil of claim 1, wherein the four legs extend from the nexus to axially forward and axially aft bolt holes on the upper surface of the outer platform. 6. The airfoil of claim 5, wherein a relative position of the axially aft bolt holes with respect to the axially forward bolt holes is defined based on a trailing edge angle of the tip section of the airfoil. 7. A fan duct comprising a plurality of circumferential arranged airfoils, wherein each of the plurality of airfoils is configured as the airfoil defined in claim 1. 8. A turbofan engine comprising the fan duct of claim 7. 9. The airfoil of claim 1, wherein the airfoil is mounted in a gas turbine engine with a cant angle between 5° and 30°, as measured from a radial direction perpendicular to an axial centerline of the gas turbine engine. 10. A vane comprising: an airfoil defined between pressure and suction surfaces, the pressure and suction surfaces extending from a leading edge of the airfoil to a trailing edge of the airfoil, the leading and trailing edges extending from a root section of the airfoil to a tip section of the airfoil;an inner platform attached to the root section, the inner platform comprising a curvilinear gusset on a lower surface of the inner platform opposite the airfoil, the curvilinear gusset extending along a camber line of the airfoil defined in the root section of the airfoil, opposite the curvilinear gusset, wherein the curvilinear gusset comprises a joint disposed proximate an aft portion of the inner platform, and wherein the joint extends in the circumferential direction and includes an axially oriented bolt hole; andan outer platform attached to the tip section of the airfoil. 11. The vane of claim 10, wherein the curvilinear gusset comprises a radially oriented bolt hole on an axially forward portion of the inner platform. 12. The vane of claim 10, wherein the outer platform comprises a multi-lobed gusset extending along an upper surface of the outer platform, opposite the tip section of the airfoil, wherein the multi-lobed gusset comprises four legs meeting at a nexus, wherein two of the four legs extend axially forward from the nexus and two of the four legs extend axially aft from the nexus. 13. The vane of claim 12, wherein the nexus of the multi-lobed gusset is positioned opposite a maximum camber point of the airfoil, the maximum camber point defined along a camber line in the tip section of the airfoil, opposite the multi-lobed gusset. 14. The vane of claim 12, wherein the legs of the multi-lobed gusset extend between axially forward and axially aft bolt holes on the upper surface of the outer platform, and wherein a relative position of the axially forward and axially aft bolt holes is defined by a trailing edge angle of the airfoil in the tip section. 15. A plurality of vanes, wherein each of the plurality of vanes is configured as the vane defined in claim 14, and wherein the plurality of vanes define two airfoil classes having different trailing edge angles at the tip sections of the airfoils. 16. The plurality of vanes as defined in claim 15, wherein the trailing edge angles of the two airfoil classes differ by at least 5° with respect to an axial direction. 17. The plurality of vanes as defined in claim 15, wherein the trailing edge angles of the two airfoil classes differ by at least 10° with respect to an axial direction. 18. A propulsion engine comprising a plurality of vanes, wherein each of the plurality of vanes is configured as the vane defined in claim 14, and wherein the plurality of vanes are circumferentially arranged about a fan duct. 19. A guide vane comprising: an airfoil extending from a leading edge to a trailing edge, the leading and trailing edges extending from a root section of the airfoil to a tip section of the airfoil;an inner platform attached to the root section of the airfoil, the inner platform comprising a curvilinear gusset extending opposite the airfoil along a camber line defined in the root section; andan outer platform attached to the tip section of the airfoil, the outer platform comprising a multi-lobed gusset having a nexus positioned opposite a maximum camber point defined in the tip section of the airfoil, wherein the multi-lobed gusset comprises two legs extending axially forward from the nexus on the outer platform and two legs extending axially aft from the nexus on the outer platform. 20. The guide vane of claim 19, wherein the inner platform comprises a radial bolt hole and the curvilinear gusset comprises a mount portion with an axial bolt hole. 21. The guide vane of claim 19, wherein the two legs extending axially forward from the nexus extend to axially forward bolt holes on an upper surface of the outer platform, and the two legs extending axially aft from the nexus extend to axially aft bolt holes on the upper surface of the outer platform, opposite the tip section of the airfoil. 22. The guide vane of claim 21, wherein a relative position of the axially aft bolt holes with respect to the axially forward bolt holes is defined by a trailing edge angle of the airfoil in the tip section. 23. A plurality of guide vanes as defined by the vane in claim 19, wherein the plurality of guide vanes define vane classes with trailing edge angles that differ by at least 5°. 24. A turbofan engine comprising a plurality of guide vanes as defined by the vane in claim 19, wherein the plurality of guide vanes are coaxially arranged about a power core comprising a compressor, a combustor and a turbine in flow series. 25. The turbofan engine of claim 24, wherein the guide vanes have a cant angle between 5° and 30° as measured from a radial direction perpendicular to a centerline of the turbofan engine.