Propeller rotor for a vertical take off and landing aircraft

Patent metadata

Field	Value
Publication number	US-10723451-B2
Application number	US-201415305039-A
Country	US
Kind code	B2
Filing date	Apr 22, 2014
Priority date	Apr 22, 2014
Publication date	Jul 28, 2020
Grant date	Jul 28, 2020

Abstract

A propeller blade is provided including a leading edge and a trailing edge. The trailing edge is arranged opposite the leading edge to form an airfoil there between. At least one of the leading edge and the trailing edge include at least one facet.

First claim

What is claimed is:

1. A propeller blade operable to rotate about an axis of rotation comprising:
a leading edge comprising a first leading edge facet intersecting with a second leading edge facet at a first non-linear angle defining a first vertex, each leading edge facet comprising a respective linear portion of the leading edge, and the first leading edge facet extending from an inboard end to the second leading edge facet; and
a trailing edge comprising a first trailing edge facet intersecting with a second trailing edge facet at a second non-linear angle defining a second vertex, each trailing edge facet comprising a respective linear portion of the trailing edge, the trailing edge being arranged opposite the leading edge and forming an airfoil there between,
the first vertex being arranged on a first plane, the second vertex being arranged on a second plane distinct from the first plane, and each plane being orthogonal to the axis of rotation.

2. The propeller blade according to claim 1 , wherein a width of at least one of the leading edge facets and trailing edge facets varies over a length of the propeller blade.

3. The propeller blade according to claim 1 , further comprising:
a plurality of leading edge facets and trailing edge facets including the first and second leading edge facets, and the first and second trailing edge facets,
wherein a number of leading edge facets is identical to a number of trailing edge facets.

4. The propeller blade according to claim 1 , further comprising:
a plurality of leading edge facets and trailing edge facets including the first and second leading edge facets, and the first and second trailing edge facets,
wherein a number of leading edge facets is different from a number of trailing edge facets.

5. The propeller blade according to claim 1 , wherein a contour of the leading edge defined by the leading edge facets is substantially identical to a contour of the trailing edge defined by the trailing edge facets.

6. The propeller blade according to claim 1 , wherein a contour of the leading edge defined by the leading edge facets is substantially different from a contour of the trailing edge defined by the trailing edge facets.

7. The propeller blade according to claim 1 , wherein the inboard end intersects with the first trailing edge facet at a third non-linear angle defining a third vertex, the third vertex being arranged on a third plane, the third plane being distinct from the first and second planes, and each plane being orthogonal to the axis of rotation.

8. The propeller blade according to claim 7 , wherein the third plane is situated inward from the first plane and the second plane.

9. The propeller blade according to claim 7 , wherein the first leading facet and the second leading edge facet are arranged at respective non-linear angles to the third plane.

10. An aircraft comprising:
an airframe;
at least one engine mounted to the airframe; and
a thrust system operably coupled to the at least one engine, the thrust system including:
a hub; and
a plurality of propeller blades, each propeller blade operable to rotate about an axis of rotation, and each blade comprising:
a leading edge comprising a first leading edge facet intersecting with a second leading edge facet at a first non-linear angle defining a first vertex, each leading edge facet comprising a respective linear portion of the leading edge, and the first leading edge facet extending from an inboard end to the second leading edge facet; and
a trailing edge comprising a first trailing edge facet intersecting with a second trailing edge facet at a second non-linear angle defining a second vertex, each trailing edge facet comprising a respective planar linear portion of the trailing edge, the trailing edge being arranged opposite the leading edge and forming an airfoil there between,
the first vertex being arranged on a first plane, the second vertex being arranged on a second plane distinct from the first plane, and each plane being orthogonal to the axis of rotation.

11. The aircraft according to claim 10 , further comprising:
a plurality of leading edge facets and trailing edge facets including the first and second leading edge facets, and the first and second trailing edge facets,
wherein a number of leading edge facets is identical to a number of trailing edge facets.

12. The aircraft according to claim 10 , wherein a contour of the leading edge defined by the leading edge facets is substantially identical to a contour of the trailing edge defined by the trailing edge facets.

13. The aircraft according to claim 10 , wherein a contour of the leading edge defined by the leading edge facets is substantially different from a contour of the trailing edge defined by the trailing edge facets.

14. The aircraft according to claim 10 , wherein the aircraft is an unmanned aerial vehicle.

15. The aircraft according to claim 10 , wherein a width of at least one of the leading edge facets and trailing edge facets varies over a length of the propeller blade.

16. The aircraft according to claim 15 , further comprising:
a plurality of leading edge facets and trailing edge facets including the first and second leading edge facets, and the first and second trailing edge facets,
wherein a number of leading edge facets is different from a number of trailing edge facets.

17. The aircraft according to claim 10 , wherein the inboard end intersects with the first trailing edge facet at a third non-linear angle defining a third vertex, the third vertex being arranged on a third plane, the third plane being distinct from the first and second planes, and each plane being orthogonal to the axis of rotation.

18. The aircraft according to claim 17 , wherein the third plane is situated inward from the first plane and the second plane.

19. The aircraft according to claim 17 , wherein the first leading facet and the second leading edge facet are arranged at respective non-linear angles to the third plane.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Alber Mark R

Classifications

• B64U50/13

  using external fans or propellers · CPC title

• B64U30/24

  Coaxial rotors · CPC title

• B64U10/17

  Helicopters (flying platforms B64U10/13) · CPC title

• B64U10/20

  Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17) · CPC title

• B64C29/02

  having its flight directional axis vertical when grounded · CPC title