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1. (WO2017034426) TUNNEL WIND TURBINE WITH A HORIZONTAL AXIS OF THE ROTOR ROTATION
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PATENT CLAIMS

1. A tunnel wind turbine with a horizontal axis of the rotor rotation, including:

- a diffuser (1) in the form of a rotating body, the wall of which has, in its axial section, the shape of a convex-concave aeronautical profile with a nose (17) directed towards inflowing air and which is supported by a wind direction bearing set (6) of a vertical rotation axis on the turbine mast, and

- a rotor (2) with blades (7) rotating in the plane of a throat (Rt) of the diffuser (1) and lower ends are connected with a hub (3) bearing mounted coaxially with the diffuser (1) and having a contour consistent with an aerodynamic profile of a nacelle (4) which is connected by ribs (5) with the diffuser (1), characterised in that the lower ends of the blades (7) are set away from the surface of the hub (3) by the dimension of the lower gap (z2), the dimension being determined by the height of the connectors (8) mounted to the lower ends of the blades (7) and to the hub (3), the dimensions of the upper gap (zl) between the upper ends of the blades (7) and the surface of the throat (Rt) and the lower gap (z2) have dimensions ranging from 0.5 to 15% of the radius of the throat ( Rt), preferably from 3 to 8%.

2. The turbine according to claim 1 characterised in that the upper gap (zl) is determined by the height of the connectors (8) fixed to the upper ends of the blades (7) and to the rotational ring (9) which rotates in a circumferential recess (10) of the diffuser (1) and the inner surface of which has a shape of the throat (Rt).

3. The turbine according to claim 1 or 2, characterised in mat the ratios of the dimensions of the upper gaps (zl) and the lower gaps (z2) to the corresponding lengths of chords (cl, c2) on the ends of blades (7) of the profiles have values ranging from 0.20 to 2.5, preferably from 0.6 to 1.2.

4. The turbine according to claim 1 , characterised in that each of the blades (7) is mounted to the hub (3) by two connectors (8) having a round cross section and which are fixed in a radial direction near endings of the profiles of the lower ends of the blades (7).

5. The turbine according to claim 2, characterised in that each of the blades (7) is mounted to the rotational ring (9) and to the hub (3) by two connectors (8) having a round cross section (d), fixed in a radial direction near the endings of the profiles of the upper end and the lower end of the blades (7).

6. The turbine according to claim 1 or 2, characterised in that the side wall of the nacelle (4) has a shape being a mirror reflection of a section of the inner surface profile of the diffuser (1), the ends of the section being determined by points of intersection of the straight line (10 parallel to the diffuser axis (O-O) and the one conducted through the front point of the advance of the nose (17) of the diffuser (1) and the point (lh,) of the inner surface in the open part of the diffuser (1).

7. The turbine according to claim 1 or 2, characterised in that the ratio of the area of the axial projection of all blades (7) on the plane of the throat (RO to the active area of flow through the throat ( Rt) has a value ranging from 0.02 to 0.30, preferably from 0.10 to 0.15.

8. Turbine according to claim 1 or 2, characterised in that the ratio of the area of the inlet hole (Ri) to the active area of flow through the throat (Rt) has a value ranging from 1.0 to 1,6, preferably from 1.20 to 1.30.

9. Turbine according to claim 1 or 2, characterised in that the ratio of the area of the inlet hole (Ri) to the area of the outlet hole (Ro) has a value ranging from 0.S to 0.9, preferably from 0.65 to 0.75.

10. Turbine according to claim 1 or 2, characterised in that the ratio of the length (Ld) of the diffuser (1) to the diameter of the throat (RO has a value ranging from 0.3 to 1.1, preferably from 0.6 to 0.8.

11. Turbine according to claim 1 or 2, characterised in that the ratio of the length (Lj) of the diffuser (1) to the diameter of the outlet hole (Ro) has a value ranging from 0.1 to 0.9, preferably from 0.4 to 0.6 whereas the length (Ld) of the diffuser (1) in relation to the diameter of the inlet hole ( Ri) has a value ranging from 0.2 to 1.0, preferably from 0.5 to 0.7.

12. The turbine according to claim 2, characterised in that the circumferential recess (10) in the diffuser (1) is formed by a round support frame (11) of a C-shaped cross section open in the direction of the diffuser (1) axis and to which there are mounted composite coatings (12, 13) determining the aeronautical profile of the diffuser (1) and the lower module (14) of the bearing set (6) of the wind direction.

13. The turbine according to claim 1 or 2, characterised in that it has an electric generator (15) built into the nacelle (4) and the rotor of which is driven from the hub (3) of the rotor (2).

14. The turbine according to claim 12, characterised in that there is a current generator (16) built within the support frame (11), with fixed magnets mounted on the outer

circumference of the rotational ring (9) and with induction coils fixed to the support frame (11).

15. The turbine according to claim 1 or 2 or 14, characterised in that the diffuser (1 ), its support frame (11), coatings (12,13) of the aeronautical profile, the rotational ring (9) and elements of the current generator (16) are divided into circumferential sections with the maximum dimensions enabling transport in standard containers, the sections being assembled by being interconnected with fasteners (18) into the required working shape of the turbine.

li straight line parallel to the diffuser axis, conducted through the front point of the noseadvance

lb point of intersection of the straight line Ij and the inner surface of the diffuser profile

P0 mechanical power of the turbine according to the exemplary embodiment of the invention

Pb mechanical power of the turbine with the same diffuser with zl = 6 mm and z2 = 0 mm