Airfoil with stress-reducing fillet adapted for use in a gas turbine engine
The present disclosure is directed toward airfoils used in gas turbine engines. More specifically, the present disclosure teaches airfoils with fillets for managing stresses in airfoils during use in gas turbine engines.
1. A gas turbine engine comprising
an engine core including a compressor assembly, a combustor assembly, and a turbine assembly,
a fan assembly including a fan rotor coupled to the engine core to be driven by the engine core, an inner guide vane assembly arranged to interact with air discharged by the fan rotor moving into the engine core, and an outer guide vane assembly arranged to interact with air discharged by the fan rotor moving around the engine core,
wherein the outer guide vane assembly includes an inner band arranged around at least a portion of a central axis and an airfoil that extends radially outward from the inner band away from the central axis, the airfoil including a sheet of material that is folded to define a leading edge of the airfoil, a pressure side of the airfoil, and a suction side of the airfoil, the sheet of material being welded along a trailing edge of the airfoil to define the trailing edge, and
wherein at least one of the pressure side and the suction side of the airfoil is shaped to form a fillet at the interface of the airfoil with the inner band, the fillet shaped to taper such that the fillet increases in height measured radially from the inner band as the fillet extends from the trailing edge along a length of the airfoil toward the leading edge of the airfoil, and
wherein the fillet has a first radial height from the inner band at the trailing edge, a second radial height from the inner band, greater than the first radial height, spaced along the length of the airfoil from the trailing edge axially between the trailing edge and an axially-located midpoint of the airfoil between the leading edge and the trailing edge, and a third radial height from the inner band at the axially-located midpoint less than the second radial height.
2. The engine of claim 1 , wherein both the pressure side and the suction side of the airfoil are shaped to form a fillet at the interface of the airfoil with the inner band.
3. The assembly of claim 1 , wherein the fillet has a first endwall width measured from the airfoil along the inner band at the trailing edge and a second endwall width measured from the airfoil along the inner band, smaller than the first endwall width, spaced along the length of the airfoil from the trailing edge.
4. The assembly of claim 1 , wherein the airfoil is swept such that an axis defined by a radial length of the airfoil forms an acute angle with the central axis aft of the airfoil.