Non-uniform blade distribution for rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-9528375-B2
Application number	US-201213689941-A
Country	US
Kind code	B2
Filing date	Nov 30, 2012
Priority date	Nov 30, 2012
Publication date	Dec 27, 2016
Grant date	Dec 27, 2016

Abstract

A translational thrust system for a rotary wing aircraft is provided including a propeller system. The propeller system includes more than one pair of propeller blades extending radially outward from a rotatable propeller hub. Each pair of propeller blades includes a first propeller blade and a second propeller blade arranged diametrically opposite one another about a circumference of the propeller hub. Each pair of propeller blades is arranged at an angle to an adjacent pair of propeller blades such that the angle is less than is the pairs of propeller blades were uniformly distributed around the circumference of the propeller hub.

First claim

The invention claimed is:

1. A translational thrust system for a rotary wing aircraft comprising:
a propeller system having at least a first pair of propeller blades and a second pair of propeller blades extending radially outward from a rotatable propeller hub, wherein each pair of propeller blades includes a first propeller blade and a second propeller blade arranged diametrically opposite one another about a circumference of the propeller hub, and the first pair of propeller blades and the second pair of propeller blades are arranged such that an angle between a first propeller blade of the first pair of propeller blades and a first propeller blade of the second pair of propeller blades is less than if the first and second pairs of propeller blades were uniformly distributed around the circumference of the propeller hub, wherein the first pair of propeller blades and the second pair of propeller blades are configured to rotate to an indexed position when the rotary wing aircraft is grounded, and a distance between a rotational axis of the propeller hub and a surface on which the rotary wing aircraft is supported when the rotary wing aircraft is grounded is less than a length of one of the propeller blades.

2. The translational thrust system according to claim 1 , wherein the first propeller blade and the second propeller blade of each pair are substantially identical.

3. The translational thrust system according to claim 1 , wherein the propeller system includes at least two pairs of propeller blades, and the angles formed between each pair of adjacent first propeller blades are generally equal.

4. The translational thrust system according to claim 1 , wherein the pairs of propeller blades are indexed about a horizontal axis such that when the hub is stationary a clearance exists between the propeller blades and the surface on which the aircraft is supported.

5. The translational thrust system according to claim 1 , wherein the propeller system is a pusher propeller system.

6. The translational thrust system according to claim 1 , wherein the first propeller blades and the second propeller blades are arranged within a plane.

7. The translational thrust system according to claim 6 , wherein each first propeller blade and each second propeller blade is configured to rotate within the plane relative to the hub.

8. A rotary wing aircraft comprising:
an airframe;
at least one rotor system;
a propeller system mounted to a tail end of the air frame, the propeller system including at least a first pair of propeller blades and a second pair of propeller blades extending radially outward from a central rotatable hub, the first pair of propeller blades and the second of propeller blades are arranged such that an angle between a first propeller blade of the first pair of propeller blades and a first propeller blade of the second pair of propeller blades is less than if the first and second pairs of propeller blades were uniformly distributed around a circumference of the propeller hub;
wherein a first vertical clearance exists between the hub and the rotor system, and a second vertical clearance exists between the hub and a surface below the rotary wing aircraft, the first vertical clearance being larger than the second vertical clearance, wherein the second vertical clearance is less than a length of one of the propeller blades.

9. The rotary wing aircraft according to claim 8 , wherein each pair of propeller blades includes a first propeller blade and a second propeller blade mounted diametrically opposite one another about the hub.

10. The rotary wing aircraft according to claim 9 , wherein the first propeller blade and the second propeller blade of each pair are substantially identical.

11. The rotary wing aircraft according to claim 9 , wherein a length of each first propeller blade and each second propeller blade is about equal to the first vertical clearance.

12. The rotary wing aircraft according to claim 9 , wherein the propeller system includes at least two pairs of propeller blades, and the angles formed between each pair of adjacent first propeller blades are generally equal.

13. The rotary wing aircraft according to claim 8 , wherein the pairs of propeller blades are indexed about a horizontal axis, parallel to the surface below the rotary wing aircraft, when the rotary wing aircraft is stationary.

14. The rotary wing aircraft according to claim 8 , wherein the propeller system is a pusher propeller system.

15. The rotary wing aircraft according to claim 9 , wherein the first propeller blades and the second propeller blades are arranged within a plane.

16. The rotary wing aircraft according to claim 15 , wherein each first propeller blade and each second propeller blade is configured to rotate within the plane relative to the hub.

Assignees

• Alber Mark R
• Sikorsky Aircraft Corp

Inventors

• Alber Mark R

Classifications

• B64C2027/8236

  including pusher propellers · CPC title

• B64C27/22

  Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft · CPC title

• B64C27/82 Primary

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• F01D5/02 Primary

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title