Low radius ratio fan for a gas turbine engine
A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.
1. A fan blade for a gas turbine engine, comprising: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side, wherein the dovetail, airfoil, and transition section are formed as a composite layup comprising a plurality of layers of fibers embedded in a matrix.
2. The fan blade of claim 1 wherein the at least one shoulder runs in a generally axial direction.
3. The fan blade of claim 1 wherein the dovetail includes a pair of opposed pressure faces.
4. The fan blade of claim 1 wherein the airfoil comprises spaced-apart leading and trailing edges extending between a root and a tip of the airfoil.
5. The fan blade of claim 1 wherein the at least one shoulder is integrally-formed with the remainder of the fan blade.
6. The fan blade of claim 1 wherein the at least one shoulder protrudes to a maximum extent at a leading edge of the fan blade, and tapers off in an axially rearward direction.
7. The fan blade of claim 1 wherein first and second shoulders protrude from the pressure and suction sides, respectively.
8. A rotor assembly comprising:
a rotor disk including an annular array of dovetail slots;
an array of fan blades each having:
a straight axial dovetail engaged in one of the dovetail slots of the rotor, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including first and second shoulders protruding from nominal surfaces of the pressure and suction sides, respectively, each shoulder including a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the respective side of the fan blade, wherein a plurality of spaces are present between adjacent fan blades, and wherein the dovetail, airfoil, and transition section are formed as a composite layup comprising a plurality of layers of fibers embedded in a matrix; and
an array of platforms disposed in the spaces between adjacent fan blades, each platform having an outer surface defining a portion of a flowpath boundary and abutting the side faces of the shoulders of adjacent blades.
9. The rotor assembly of claim 8 wherein the shoulders run in a generally axial direction.
10. The rotor assembly of claim 8 wherein the dovetail includes a pair of opposed pressure faces.
11. The rotor assembly of claim 8 wherein the airfoil comprises spaced-apart leading and trailing edges extending between a root and a tip of the airfoil.
12. The rotor assembly of claim 8 wherein the shoulders are integrally-formed with the remainder of the fan blade.
13. The rotor assembly of claim 8 wherein the shoulders protrude to a maximum extent at a leading edge of the fan blade, and taper off in an axially rearward direction.