Ducted thrust producing system with asynchronous fan blade pitching
An actuation assembly for a variable pitch fan for a gas turbine engine is provided. The actuation assembly generally includes a plurality of fan blades, a scheduling ring, and a plurality of linkage arms. The plurality of fan blades are rotatably coupled to a disk and extend radially therefrom. The scheduling ring is rotatable relative to the disk and has a plurality of slots. Each of the plurality of linkage arms are operatively coupled to one of the plurality of fan blades and to one of the plurality of slots. Each of the plurality of fan blades rotate according to a blade pitch schedule defined by the slot to which it is operatively coupled, and at least two of the plurality of slots define different blade pitch schedules.
1. An actuation assembly for a variable pitch fan for a gas turbine engine, the actuation assembly comprising:
a plurality of fan blades rotatably coupled to a disk and extending axially therefrom;
a scheduling ring rotatable relative to the disk and having a plurality of slots; and
a plurality of linkage arms, each linkage arm operatively coupled to one of the plurality of fan blades and to one of the plurality of slots,
wherein each of the plurality of fan blades rotates according to a blade pitch schedule defined by the slot to which it is operatively coupled, and wherein at least two of the plurality of slots define different blade pitch schedules, wherein each fan blade rotates on a different blade pitch schedule than adjacent fan blades.
2. The actuation assembly of claim 1 , wherein each of the plurality of linkage arms has a first end fixedly connected to one of the plurality of fan blades and a second end slidably connected to one of the plurality of slots.
3. The actuation assembly of claim 1 , wherein the variable pitch fan comprises between eight and twenty fan blades rotatably coupled to the disk.
4. The actuation assembly of claim 1 , wherein the variable pitch fan comprises twelve fan blades.
5. The actuation assembly of claim 1 , wherein a first set of fan blades rotate according to a first blade pitch schedule and a second set of fan blades rotate according to a second blade pitch schedule, and wherein the first set of fan blades and the second set of fan blades do not rotate through flat pitch at the same time.
6. The actuation assembly of claim 5 , wherein the first blade pitch schedule and the second blade pitch schedule are the same except when rotating through flat pitch.
7. The actuation assembly of claim 5 , wherein the first blade pitch schedule and the second blade pitch schedule are different in the reverse thrust position.
8. The actuation assembly of claim 1 , wherein an electric motor rotates the scheduling ring relative to the disk.
9. The actuation assembly of claim 1 , wherein the variable pitch fan has a blade solidity greater than one.
10. The actuation assembly of claim 1 , wherein the variable pitch fan is used in a ducted gas turbine engine configuration.
11. A ducted gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
a core engine;
a variable pitch fan arranged in flow communication with the core engine, the variable pitch fan including a disk and a plurality of fan blades coupled to the disk and extending in a radial direction, the disk and the plurality of fan blades configured to rotate about the axial direction of the ducted gas turbine engine; and
an actuation assembly configured to change the pitch of the plurality of fan blades about the radial direction, the actuation assembly comprising:
a scheduling ring defining a first plurality of slots corresponding to a first blade pitch schedule and a second plurality of slots corresponding to a second blade pitch schedule; and
a plurality of linkage arms, each linkage arm having a first end fixedly connected to one of the plurality of fan blades and a second end slidably coupled to one of the first or second plurality of slots,
wherein the plurality of fan blades rotate according to the first or second blade pitch schedule as the scheduling ring is rotated relative to the disk, wherein each fan blade rotates on a different blade pitch schedule than adjacent fan blades.
12. The ducted gas turbine engine of claim 11 , wherein the variable pitch fan comprises between eight and twenty fan blades rotatably coupled to the disk.
13. The ducted gas turbine engine of claim 11 , wherein the variable pitch fan comprises twelve fan blades.
14. The ducted gas turbine engine of claim 11 , wherein a first set of fan blades rotates according to the first blade pitch schedule and a second set of fan blades rotates according to the second blade pitch schedule, and wherein the first set of fan blades and the second set of fan blades do not rotate through flat pitch at the same time.
15. The ducted gas turbine engine of claim 14 , wherein the first blade pitch schedule and the second blade pitch schedule are the same except when rotating through flat pitch.
16. The ducted gas turbine engine of claim 11 , wherein the first blade pitch schedule and the second blade pitch schedule are different in the reverse thrust position.
17. The ducted gas turbine engine of claim 11 , wherein an electric motor rotates the scheduling ring relative to the disk.
18. The ducted gas turbine engine of claim 11 , wherein the variable pitch fan has a blade solidity greater than one.