Propulsor fan array
A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blades. The plurality of blades are tensioned at tips of the plurality of blade fans such that a pitch of the blades during thrust generation is substantially the same as a pitch of the blades at rest. By tensioning the tips of the blades, an angle of the blades is maintained during operation of the propulsor fan thereby reducing noise that may result from changes in the angle of the blades.
1. A propulsor fan array comprising:
a plurality of propulsor fans configured to collectively generate thrust, each propulsor fan of the plurality of propulsor fans comprising:
a blade fan having a plurality of blades, wherein a tip of each blade of the plurality of blades is tensioned such that a pitch of the plurality of blades during thrust generation is substantially the same as a pitch of the plurality of blades at rest; and
a tension ring comprising a body and a plurality of openings in the body, each opening of the plurality of openings extending through an entire radial thickness of the body of the tension ring,
wherein each blade of the plurality of blades comprises a first end, a second end, and an airfoil between the first end and the second end, wherein the first end of each blade of the plurality of blades is disposed within a corresponding one of the plurality of openings of the tension ring to maintain the pitch of the plurality of blades during thrust generation to be substantially the same as the pitch of the plurality of blades at rest, and
wherein a width of the first end of each blade of the plurality of blades that is disposed within the corresponding one of the plurality of openings is wider than a first end of the airfoil from which the first end of the blade extends where the first end of the airfoil is not disposed within the corresponding one of the plurality of openings.
2. The propulsor fan array of claim 1 , wherein the plurality of blades are arranged in a circular ring, and the second end of each blade of the plurality of blades is closer to a center of the circular ring than the first end of each blade.
3. The propulsor fan array of claim 1 , wherein each of the plurality of propulsor fans comprise a duct that at least partially surrounds the blade fan.
4. The propulsor fan array of claim 1 , wherein the plurality of blades includes more than five blades.
5. The propulsor fan array of claim 4 , wherein the plurality of blades includes at least 20 blades and at most 840 blades.
6. The propulsor fan array of claim 2 , wherein the first end of each blade of the plurality of blades comprises a first locking end at the first end of the airfoil and the second end of each blade of the plurality of blades comprises a second locking end at a second end of the airfoil that is opposite the first end of the airfoil, the second end of the airfoil closer to the center of the circular ring formed by the plurality of blades; and
wherein a width of the first locking end in a first direction and a thickness of the first locking end in a second direction that is different from the first direction are respectively greater than a width of the first end of the airfoil in the first direction and a thickness of the first end of the airfoil in the second direction, and a width of the second locking end in the first direction and a thickness of the second locking end in the second direction are respectively greater than a width of the second end of the airfoil in the first direction and a thickness of the second end of the airfoil in the second direction.
7. The propulsor fan array of claim 6 , wherein the first locking end of each blade of the plurality of blades is configured to tension the tip of the respective blade by being directly in contact with the body of the tension ring while disposed in the corresponding one of the plurality of openings of the tension ring.
8. The propulsor fan array of claim 1 , wherein each blade of the plurality of blades is partially overlapped by at least another one of the plurality of blades.
9. The propulsor fan array of claim 6 , wherein each propulsor fan of the plurality of propulsor fans further comprises a locking ring configured to connect to the blade fan, the locking ring comprising:
a first end having a first diameter;
a second end that is opposite the first end, the second end having a second diameter that is greater than the first diameter;
a plurality of protrusions that extend from the first end of the locking ring towards the second end of the locking ring;
a plurality of slots at the first end of the locking ring, each slot of the plurality of slots disposed between a pair of protrusions from the plurality of protrusions; and
a plurality of threads in an inner surface of the locking ring, the plurality of threads extending from the second end of the locking ring to ends of the plurality of slots.
10. The propulsor fan array of claim 9 , wherein each second locking end is disposed within a corresponding one of the plurality of slots of the locking ring to directly connect the locking ring to the blade fan.
11. The propulsor fan array of claim 10 , wherein each second locking end is in direct contact with the pair of protrusions that form a slot in which the second locking end is disposed to maintain a pitch of a root of each blade of the plurality of blades during thrust generation and while at rest without contacting another second locking end of the plurality of blades.
12. An aircraft comprising:
a fuselage;
a plurality of wings connected to the fuselage; and
a plurality of propulsor fan arrays, each of the plurality of propulsor fan arrays integrated into a corresponding one of the plurality of wings and comprising:
a plurality of propulsor fans configured to collectively generate thrust of the aircraft, each propulsor fan of the plurality of propulsor fans comprising:
a blade fan having a plurality of blades, wherein a tip of each blade of the plurality of blades is tensioned such that a pitch of the plurality of blades during thrust generation is substantially the same as a pitch of the plurality of blades at rest; and
a tension ring comprising a body and a plurality of openings in the body, each opening of the plurality of openings extending through an entire radial thickness of the body of the tension ring,
wherein each blade of the plurality of blades comprises a first end, a second end, and an airfoil between the first end and the second end, wherein the first end of each blade of the plurality of blades is disposed within a corresponding one of the plurality of openings of the tension ring to maintain the pitch of the plurality of blades during thrust generation to be substantially the same as the pitch of the plurality of blades at rest, and
wherein a width of the first end of each blade of the plurality of blades that is disposed within the corresponding one of the plurality of openings is wider than a first end of the airfoil from which the first end of the blade extends where the first end of the airfoil is not disposed within the corresponding one of the plurality of openings.
13. The aircraft of claim 12 , wherein the plurality of blades are arranged in a circular ring, and the second end of each blade of the plurality of blades is closer to a center of the circular ring than the first end of each blade.
14. The aircraft of claim 12 , wherein the plurality of blades includes more than five blades.
15. The aircraft of claim 13 , the first end of each of blade the plurality of blades comprises a first locking end at the first end of the airfoil and the second end of each blade of the plurality of blades comprises a second locking end at a second end of the airfoil that is opposite the first end of the airfoil, the second end of the airfoil closer to the center of the circular ring formed by the plurality of blades; and
wherein a width of the first locking end in a first direction and a thickness of the first locking end in a second direction that is different from the first direction are respectively greater than a width of the first end of the airfoil in the first direction and a thickness of the first end of the airfoil in the second direction, and a width of the second locking end in the first direction and a thickness of the second locking end in the second direction are respectively greater than a width of the second end of the airfoil in the first direction and a thickness of the second end of the airfoil in the second direction.
16. The aircraft of claim 15 , wherein the first locking end of each blade of the plurality of blades is configured to tension the tip of the respective blade by being directly in contact with the body of the tension ring while disposed in the corresponding one of the plurality of openings of the tension ring.
17. The aircraft of claim 15 , wherein each propulsor fan of the plurality of propulsor fans further comprises a locking ring configured to connect to the blade fan, the locking ring comprising:
a first end having a first diameter;
a second end that is opposite the first end, the second end having a second diameter that is greater than the first diameter;
a plurality of protrusions that extend from the first end of the locking ring towards the second end of the locking ring;
a plurality of slots at the first end of the locking ring, each slot of the plurality of slots disposed between a pair of protrusions from the plurality of protrusions; and
a plurality of threads in an inner surface of the locking ring, the plurality of threads extending from the second end of the locking ring to ends of the plurality of slots.
18. The aircraft of claim 17 , wherein each second locking end is disposed within a corresponding one of the plurality of slots of the locking ring to connect the locking ring to the blade fan.
19. The aircraft of claim 18 , wherein each second locking end is in direct contact with the pair of protrusions that form a slot in which the second locking end is disposed to maintain a pitch of a root of each blade of the plurality of blades during thrust generation and while at rest without contacting another second locking end of the plurality of blades.
20. The aircraft of claim 17 , further comprising:
a hub having a first end and a second end, the hub including a plurality of threads that extend from the second end of the hub towards the first end of the hub without extending to the first end of the hub,
wherein the second end of the hub is inserted into the second end of the locking ring such that the plurality of threads of the hub are connected to the plurality of threads of the locking ring.