Utilization of wind energy

Claim 2

A wind energy device comprising a first airfoil having a major axis, a leading edge, a trailing edge, and a tip, the first airfoil being supported above a surface and being adapted, when traversed by a prevailing wind, to generate a vortex at its tip, means to vary the orientation of the airfoil relative to the prevailing wind, and a rotary device located in the path of the vortex and adapted to be driven by the wind in the vortex, including a second airfoil having a major axis generally transverse to the major axis of the first airfoil and arrranged so that its downwash effect augments the energy of the vortex.

Claim 3

A device as claimed in claim 1, wherein the first airfoil is a low aspect-ratio, slow-speed, high-lift airfoil.

Claim 4

A device as claimed in claim 1, wherein the second airfoil has a leading edge and a trailing edge and adjustment means are provided to vary the angle between a line joining the leading and trailing edges and the axis of the vortex generated at the first airfoil tip.

Claim 5

A device as claimed in claim 3, wherein said adjustment means automatically adjusts the angle of attack of the second airfoil when the angle of attack of the first airfoil is varied.

Claim 6

A device as claimed in claim 3, wherein the second airfoil is hinged to the first airfoil about an axis extending along the leading edge of the second airfoil.

Claim 7

A device as claimed in claim 3, wherein the second airfoil is cut away adjacent the first airfoil to permit spanwise flow along the first airfoil.

Claim 8

A device as claimed in claim 3, wherein the second airfoil is a low aspect-ratio, slow-speed, high-lift airfoil.

Claim 9

A device as claimed in claim 1, wherein the rotary device is a vertical axis rotary device.

Claim 10

A device as claimed in claim 1, wherein the rotary device includes at least one Savonius rotor arranged with its axis substantially parallel to a generatrix of the conical shape of the vortex.

Claim 11

A device as claimed in claim 1, wherein the rotary device is a Savonius rotor arranged with its axis in a position where, in use, the axis of the vortex will lie.

Claim 12

A device as claimed in claim 1, wherein the trailing edge of the first airfoil has a barrier wall forming a barrier to airflow across the airfoil on the high pressure side thereof.

Claim 13

A device as claimed in claim 1, wherein the first airfoil has a dihedral angle larger than the dihedral angle used for an aeroplane.

Claim 14

A device as claimed in claim 12, wherein the dihedral angle is 13° or more.

Claim 15

A device as claimed in claim 1, wherein the corner of the first airfoil formed by the trailing edge and the tip is cut away, so that the rotary device can be placed as close as possible to the origin of the tip vortex.

Claim 16

A device as claimed in claim 1, wherein a plate having an aperture therethrough closes the high pressure side of the airfoil at the tip, the aperture enabling air to escape from the high pressure side to the low pressure side of the airfoil in order to define the origin of the tip vortex.

Claim 17

A device as claimed in claim 15, wherein said plate comprises means to adjust the size of the aperture.

Claim 18

A device as claimed in claim 1, wherein the first airfoil includes a step in its leading edge, the step being such that the leading edge on the side of the step nearer the tip is set back relative to the leading edge on the side of the step nearer the root.

Claim 19

A device as claimed in claim 1, wherein the rotary device is attached to the airfoil tip at the trailing edge, and means are provided for adjusting its position relative to the airfoil.

Claim 20

A device as claimed in claim 1, wherein an air deflector is provided on the low pressure side of the first airfoil, said air deflector being adapted to deflect wind away from the air foil tip.

Claim 21

A device as claimed in claim 1, including two first airfoils arranged symmetrically to one another with their roots adjacent and their tips remote from one another.

Claim 22

A device as claimed in claim 1, wherein the first airfoil profile is substantially as defined by the co-ordinates of the following Table: ______________________________________ Upper Surface Lower Surface Station as % of Chord as % of Chord ______________________________________ 0 -4.59 -6.31 1 -1.02 -7.94 2 +1.17 -8.13 3 +2.82 -8.06 4 +4.19 -7.77 5 +5.37 -7.29 6 +6.38 -6.77 8 +8.35 -5.57 10 +9.95 -4.32 15 +13.12 -0.81 20 +15.15 +3.30 25 +16.46 +6.86 30 +17.38 +9.57 35 +17.83 +11.10 40 +17.96 +11.90 45 +17.72 +11.94 50 +16.94 +11.63 60 +14.57 +10.36 70 +11.50 +8.55 80 +8.46 +6.14 90 +5.08 +3.23 100 +1.12 +0.00 ______________________________________

Claim 25

A method as claimed in claim 22, including the step of applying heat to the high pressure side of the first airfoil adjacent the tip thereof.