IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0462149
(2009-07-30)
|
등록번호 |
US-8317480
(2012-11-27)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
22 |
초록
▼
A turbine assembly comprises 2 or more symmetrical vanes or blades attached to a centralized shaft. The assembly may be placed into a fluid current for transferring energy therefrom. Each blade has a scoop with a relatively broader span at the top end and a relatively narrow span at the bottom, whic
A turbine assembly comprises 2 or more symmetrical vanes or blades attached to a centralized shaft. The assembly may be placed into a fluid current for transferring energy therefrom. Each blade has a scoop with a relatively broader span at the top end and a relatively narrow span at the bottom, which scoop-like vane or blade resembles an inverted tear drop. Eighty-six percent of the potential energy vector is captured within the blade assembly. One end may be connected to a power generation device that will create electrical power when rotated. Certain energy transferring methodology is believed further supported by the vane or blade designed incorporated into the overall turbine assembly.
대표청구항
▼
1. A turbine assembly for transferring energy from a fluid current, the turbine assembly comprising: a central shaft, the central shaft being rotatable about an axis of rotation; anda series of vanes, the vanes each being attached to the central shaft with substantially equal spacing therebetween, t
1. A turbine assembly for transferring energy from a fluid current, the turbine assembly comprising: a central shaft, the central shaft being rotatable about an axis of rotation; anda series of vanes, the vanes each being attached to the central shaft with substantially equal spacing therebetween, the vanes each having an inverted tear drop shape, and thus comprising a C-shaped cross section through a first plane orthogonal to the axis of rotation and an inverted J-shaped cross section through a second plane parallel to the axis of rotation, said C-shaped and J-shaped cross sections each having a convex outer surface, a concave inner surface, a radially inner edge, and a radially outer edge, the convex outer surfaces each opposing and abutting the central shaft at superior vane portions and the inner radial edges opposing and abutting the central shaft at inferior vane portions, the concave inner surfaces for capturing a directed fluid current and the convex outer surfaces for deflecting said current, the concave inner surfaces and convex outer surfaces respectively being associated with first and second current pressures, the first current pressure being greater than the second current pressure for imparting a torque through the axis of rotation and rotating the central shaft. 2. The turbine assembly of claim 1 wherein the convex outer surfaces each helically wrap around a portion of the central shaft for deflecting the fluid current into the concave inner surfaces such that the concave inner surfaces capture deflected fluid current for increasing the first current pressure relative to the second current pressure. 3. The turbine assembly of claim 2 comprising bridge portions, the bridge portions connecting the radially inner edges of a series of first vanes to the convex outer surfaces of a series of second vanes, the bridge portions and convex outer surfaces of the series of vanes enclosing a transverse space about the central shaft, the bridge portions and convex outer surfaces thus for reducing drag between adjacent vanes. 4. The turbine assembly of claim 3 wherein the bridge portions direct deflected fluid current from the convex outer surfaces to the concave inner surfaces. 5. The turbine assembly of claim 1 wherein each vane comprises a pointed inferior terminus, a rounded superior terminus, and a sloped radially outer edge extending intermediate the inferior and superior termini. 6. The turbine assembly of claim 5 wherein the superior termini are separated by a V-shaped gap, each gap for reducing drag on the turbine assembly. 7. The turbine assembly of claim 1 wherein each vane comprises a center of curvature and a line of curvature, the centers of curvature being located at the upper third of the concave inner surfaces, the lines of curvature extending inwardly from the centers of curvature towards the central shaft. 8. The turbine assembly of claim 5 wherein the vanes function to capture directed fluid current intermediate a direction range, the direction range beginning in the axial direction from the inferior terminus and extending upwardly 155 degrees from the axial direction. 9. A method for transferring energy from a fluid current, the method comprising the steps of: providing a turbine assembly, the turbine assembly comprising a shaft and at least two vanes attached to the shaft, the shaft having an axis of rotation, the vanes each having convex surfacing, concave surfacing, a radially inner edge, and a radially outer edge, the convex surfacing opposing and abutting the shaft at superior vane portions and the inner radial edges opposing and abutting the central shaft at inferior vane portions, the convex and concave surfacing having a J-shaped cross-section parallel to the axis of rotation and a C-shaped cross-section orthogonal to the axis of rotation;directing a fluid current against the concave surfacing;directing the fluid current along the concave surfacing away from the shaft; andcreating a torque coaxial with the shaft via the directed fluid current, the torque for transferring energy from the fluid current. 10. The method of claim 9 wherein the turbine assembly comprises at least three vanes, the method comprising the further steps of: directing the fluid current against both the concave and convex surfacing;directing the fluid current along the convex surfacing toward and away from the shaft; andimparting a first current pressure against the concave surfacing and a second current pressure against the convex surfacing via the directed fluid current, the first current pressure being greater than the second current pressure. 11. The method of claim 10 wherein the step of directing the fluid current along the convex surfacing toward the shaft comprises the step of directing the fluid current into the concave surfacing of an adjacent vane. 12. The method of claim 10 wherein adjacent vanes comprise bridge portions, the bridge portions connecting the radially inner edge of a first vane to the convex surfacing of an adjacent vane, the bridge portions and convex surfacing enclosing a transverse space about the shaft, the bridge portions for bridge-directing the fluid current from the convex surfacing to the concave surfacing. 13. A method for transferring energy from a fluid current, the method comprising the steps of: attaching a series of vanes to a shaft to provide a turbine assembly which enables the shaft to have an axis of rotation;providing the series of vanes each with convex surfacing, concave surfacing, a radially inner edge, and a radially outer edge, the convex surfacing opposing the shaft at superior vane portions and the inner radial edges extending from the shaft at inferior vane portions, the convex and concave surfacing having a J-shaped cross-section parallel to the axis of rotation and a C-shaped cross-section orthogonal to the axis of rotation;directing the fluid current against and along the concave surfacing away from the shaft; anddirecting the fluid current along the shaft creating a torque coaxial with the shaft, and utilizing the torque from the fluid current to transfer the energy from the fluid current. 14. The method of the claim 13 wherein, the method comprises the further steps of directing the fluid current against both concave and convex surfacing. 15. An assembly for transferring energy from a fluid current, the assembly comprising: a central shaft, the central shaft being rotatable about an axis of rotation; andfirst and second vanes, the first and second vanes each being attached to the central shaft and comprising a C-shaped cross section through a first plane, a J-shaped cross section through a second plane, and bridge portions, the second plane being parallel to the axis of rotation, said first and second planes being orthogonal to one another, said cross sections each having a convex surface and a concave surface with a radially inner edge and a radially outer edge therebetween, the convex surfaces each opposing the central shaft at superior vane portions and the inner radial edges extending from the central shaft at inferior vane portions, the bridge portions connecting the radially inner edge of the first vane to the convex outer surface of the second vane adjacent the first vane, the bridge portions and convex outer surfaces of the first and second vanes enclosing a transverse space about the central shaft, the bridge portions and convex outer surfaces for reducing drag between the adjacent vanes, the concave surfaces for capturing a directed fluid current and the convex surfaces for deflecting said current, the concave surfaces and convex surfaces respectively being associated with first and second current pressures, the first current pressure being greater than the second current pressure for imparting a net rotative force to the central shaft for rotating the shaft about the axis of rotation. 16. The turbine assembly of claim 15 wherein the bridge portions direct deflected fluid current from the convex surfaces to the concave surfaces. 17. The turbine assembly of claim 15 wherein the convex surfaces deflect the fluid current into the concave surfaces such that the concave surfaces capture deflected fluid current for increasing the first current pressure relative to the second current pressure. 18. The turbine assembly of claim 15 wherein each vane comprises a pointed inferior terminus, a rounded superior terminus, and a sloped radially outer edge extending intermediate the inferior and superior termini. 19. The turbine assembly of claim 15 wherein each vane comprises a center of curvature, the centers of curvature being located at the upper third of the concave surfaces. 20. The turbine assembly of claim 19 wherein each vane comprises a line of curvature, the lines of curvature extending inwardly from the centers of curvature towards the central shaft. 21. The turbine assembly of claim 18 wherein the vanes function to capture directed fluid current intermediate a direction range, the direction range beginning in the axial direction from the inferior terminus and extending 155 degrees from the axial direction.
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