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1. WO2021046539 - HÉLICE

Note: Texte fondé sur des processus automatiques de reconnaissance optique de caractères. Seule la version PDF a une valeur juridique

[ EN ]

I claim:

1. A propeller comprising:

a hub operable to rotate about an axis of rotation in a direction of rotation, characterized by a forward end and an aft end; and

one or more blades characterized by a root, a tip, a leading edge and a corresponding trailing edge, a thrust surface, wherein

the thrust surface of each blade conforms to a surface of a reference cone characterized by a vertex and a base, and a generator line, wherein a radial axis extending radially from the root of the blade corresponds to a generator line of the cone, and the root of each blade is fixed to the hub such that the axis of rotation lies in the same plane as the radial axis of each blade; wherein

2. The propeller of claim 1 wherein:

each blade subtends 90° or less of the reference cone circumference, and more preferably 45° or less of the reference cone circumference.

3. The propeller of claim 1 wherein:

the blade's axis of rotation intersects a generator line at a distance of at least half the length of the distance from the blade root to tip as measured along the generator line that passes through the axis of rotation and up to approximately the length of the blade's radial axis away from the cone's vertex.

4. The propeller of claim 2 wherein:

the blade's axis of rotation intersects a generator line at a distance of at least half the length of the distance from the blade root to tip as measured along the generator line that passes through the axis of rotation and up to approximately the length of the blade's radial axis away from the cone's vertex.

5. The propeller of claim 3 wherein:

each blade subtends 90° or less of the reference cone circumference, and more preferably 45° or less of the reference cone circumference.

6. The propeller of claim 1 wherein:

the axis of rotation and the axis of each blade are substantially perpendicular.

7. The propeller of claim 1 wherein:

the axis of rotation and the axis of each blade are set at an angle of 45° or more.

8. The propeller of claim 1 wherein:

the leading edge of each blade is forward of its corresponding trailing edge.

9. The propeller of claim 1 wherein:

each blade is rotated about its generator line such that its average pitch angle relative to the hub is different from that which it would have had without such rotation.

10. The propeller of claim 1 wherein

the average pitch angle between leading and trailing edges is 45° or less.

11. The propeller of claim 1 wherein:

a line on the thrust surface, along the radial axis of each blade, is a straight line corresponding to a generator line of the cone.

12. The propeller of claim 1 wherein:

a leading-to-trailing line on the thrust surface of each blade, perpendicular to the radial axis, is a circular arc.

13. The propeller of claim 1 wherein:

each blade is symmetric about a radial axis of the blade.

14. The propeller of claim 1 wherein:

each blade is asymmetric about a radial axis of the blade .

15. The propeller of claim 1 wherein:

the plane containing the radial axis and axis of rotation is substantially parallel to a plane containing a portion of the trailing edge of the blade.

16. The propeller of claim 1 wherein:

the hub is spaced apart from the vertex of the reference cone .

17. The propeller of claim 1 wherein:

a plane which passes through a portion of the blade near its trailing edge is substantially parallel to a plane containing the radial axis of the blade and its axis of rotation.

18. A propeller comprising:

a blade having a thrust face which substantially conforms to area of the curved surface of a cone;

said blade being disposed with respect to the propeller axis so that a plane containing the propeller axis will also contain a generator line of the cone which corresponds to a long axis of the blade.

19. The propeller of claim 18 wherein:

the blade has a circular curvature in directions transversely between the leading and trailing edges of the blade and no curvature in a direction radially of the blade.

20. The propeller of claim 18 wherein:

the blade has the curvature of a conic section in directions transversely between the leading and trailing edges of the blade and no curvature along a radius of the blade.

21. The propeller of claim 18 wherein:

the blade, in addition to being disposed with respect to the propeller axis so that a plane containing the propeller axis will also contain a generator line of the cone which corresponds to a long axis of the blade, is disposed such that the generator line of the cone is perpendicular to the propeller axis.

22. The propeller of claim 1 wherein:

the blade, in addition to being disposed with respect to the propeller axis so that a plane containing the axis will also contain generator line of the cone which corresponds to a long axis of the blade, is disposed such that the generator line of the cone is angled relative to the propeller axis such that the tip of the blade is forward or aft of the root of the blade.

23. The propeller of claim 1 wherein:

the axis of rotation and the axis of each blade generator line through such axis are substantially perpendicular.

24. The propeller of claim 1 wherein:

the axis of rotation and the axis of each blade generator line through such axis are set at an angle of 45° or more.

25. A propeller comprising:

a hub operable to rotate about an axis of rotation in a direction of rotation, characterized by a forward end and an aft end; and

one or more blades characterized by a root, a tip, a leading edge and a corresponding trailing edge, and a thrust surface,

wherein the thrust surface of each blade conforms to the surface of a reference cone characterized by a vertex, a base, and generator lines,

wherein an angle whose vertex lies on a plane perpendicular to the axis of rotation at a point where it intersects the thrust surface, and on an imaginary cylinder concentric with the axis of rotation, having one side of the angle in the plane of rotation and perpendicular to the radius, and the other side tangent to the imaginary cylinder at the point of intersection with the thrust surface, is no more than 90° apart from any other such angle at the same radius on the thrust surface.

26. The propeller of claim 25 wherein:

such angles are no more than 45° apart.