CA1187808A - Turbine - Google Patents
TurbineInfo
- Publication number
- CA1187808A CA1187808A CA000401691A CA401691A CA1187808A CA 1187808 A CA1187808 A CA 1187808A CA 000401691 A CA000401691 A CA 000401691A CA 401691 A CA401691 A CA 401691A CA 1187808 A CA1187808 A CA 1187808A
- Authority
- CA
- Canada
- Prior art keywords
- vanes
- aero
- turbine
- fluid
- foil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Wind Motors (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE:
A wind turbine comprising a rotor mounted in a housing, aero-foil blades on the rotor extending in cantilever fashion forwardly of the rotor to be parallel to the axis of the rotor. The blades carry at their free ends a rotatable fairing of aero-foil section so that the blades are situated at the centre of lift of the aero-foil section so that the air flows through the blades to the area of lower air pressure.
A wind turbine comprising a rotor mounted in a housing, aero-foil blades on the rotor extending in cantilever fashion forwardly of the rotor to be parallel to the axis of the rotor. The blades carry at their free ends a rotatable fairing of aero-foil section so that the blades are situated at the centre of lift of the aero-foil section so that the air flows through the blades to the area of lower air pressure.
Description
~L8';~
Tllis inverltion reLates to a ~luicl tnrbirle, more particularly to a wind turbine althougll ;t may a]so be clriven by other fluids such as water.
BACKGROUND OF THE rNVENTION
_ _ _ 5- Units for e~tracting the power from the wind have been known for centuries Eor driving mills, pumping water and the like. However these were very inefficient and had to be large in order to produce the required power.
ln- Of recent years turbines ha e been developed in order to achieve greater efficiency from smaller units. Australian Patent number 513,247 discloses a wind turbine assembly having a rotor with a plurality of vanes in radially spacecl relation to the axis, and flow controlling duct means to 15~ conduct a radial outflow of air against the vanes, the turbine havi-ng an aero-Eoil surface formecl on atl inlet duct, the vanes being situated in a low p~-ess~lre area at the trailing edge of the aero--foil.
Australian Patent AppL;cation number 213,391/77 cliscloses 20- a turbine rotor having vanes mountecl in a convergent-divergent duct, flow channels through the duct wal] controLling the boundary layer.
Australian Patent number 492,087 shows a wind turbine having a duct in which ls mounted stator and rotor blades.
25. It is an object of this invention to provide an improved willd turbine hav;ng advantages over the known art, in that ; it is more effective Ln converting the wind energy lnto motive power.
It is a further object to provide a wind turbine which is effective in delivering power from winds of low velocity.
.. , `~
SUMMARY OE l'llEi lNVEN'[`~ON
There is pro~ided according to the invention a fluid turbine to deliver power extracted from the fluid, a turbine havi.ng a rotor mounted ~or rotation about a axis parallel to 5- the flow, a plurality of vanes carri.ed by said rotor, a housing having in cross-section an aero-Eoil section, said vanes being situated in a passage through the aero-foil section at a position corresponding generally to the centre of lift of the aero-foil section whereby fl.uid flows from the high pressure 10. area to the low pressure area o~ the aero-foil section through the passage to thus act on the turbi.ne blades.
BRIEF DESCRIPTlON OF THE DRAWING~
Figure l i.s a perspective vi.ew of a turbine according to the invention.
15- Figure 2 is a cross-sectional view of the turbine.
Figure 3 is a d.iagramatic-sectional view of the invention.
Figure 4 is a diagramatic part-sectiona]. view of the vanes on the rotor, and Figure 5 is a perspective view of one vane.
20. DESCRIPTION OF T~IE PREE ERRED EMBODIMENT
Referring to the drawings tElere is shown a turbine 1 having a rotor 2 mounted on a shaft 3 supporting a bearing 4. Beari.ng 4.is supported on a frame 5, the turbine ~
being mounted on a shaft supported in a bearing 7. The ~5- drive from the turbine wheel 2 can in this embodiment be by a friction whee]. 8 attached to a drive shaft 9 which passes dowllwardly through the pedestal 6 and from which motive power may be obtained.
7~)8 The tnrbine wheel. 2 earrLes a plurality of vanes 10 to whi.ch are attflche(l a Eorwar(l fa:irl'llg ll.
The turbirle 1 also inc]udes a hollow aerodynamically shaped bod~ 12, a tai] portion 13 being prov:i.ded so that 5. the turbine unit will be qu;.ckl~ orientated into the pre-vai].ing air fiow~
Turning now to ~igure 3 the-re is shown a aero-foil ,section 14 having an upper surface 15, lower surface 16, ~~' leading edge 17 and trailing edge 18. As is known with lO. aero-foil sections, there is a reduced pressure formed over the upper surface and that there is an area or portion at which the centre of pressure is considered to act. If now it is considered that a duct or passage 19 is formed through the aero-foil section at the centre of pressure, that the air flow 15. forming Lhe reduced pressure above the aero-foil will cause a flow of fl~lid through the passage into the area of reduced pressure. This,~concept is utilised in the present invention and it wilL be seen that the fa:iring ll merges into the housing l2 to form an aero-foi]. shape, the fairing 11 being curved 20. in an aero~foil. section.
- .
The turbine wheel 2 is also provided with a conical deflecting surface 20 which also ;.s mounted on the shaft 3 and joins to the turbine wheel adjacent to the vanes The vanes 10 are attached to the turbine whee~ and 25. extend forwardly in cantilever fashion~ the vanes carryi.ng at their forward end the fairing 11 which thus rotates with the vanes. As shown in Figures ~ and 5 the vanes 10 are formed in this example of sheet metal with end flanges 21 by which the vanes are mounted on the turbine whee]
3~. 2 and to which the fairing is attached. It has been found that each of the vanes subtend an angle in the order of ~ , .
~3'78~8 8 to 16 degrees, but preEerabLy 12 clegrees and it is preferred that each vane of a cord length in the vicinity of lOOmm at least; for it is we11 known i.n the model aircraft art that this is the mir1imum cord ]ength wh:i.cil is required to achieve 5. satisfactory liLt and performance.
Each of the blades is shaped so that the leading edge is straight for approximately one third of its length along the line angle A-B, and similarly the trailing edge is straight for approximately one third of its length along lO. the line angle B-C.
The chord line A-C is preferably sltuated between 50 and 60 degrees but more particularly 56 degrees from the radial line, ancl the l.eadin~ edge angle A-B is situated between 30 and 40 degrees frorn the chord line, more 15. particularly 37 degrees, with the trailing edge line B-C being situated between 75 and 85 degrees, more parti.cularly 7 degrees from the radial line.
Wi.th the blades so arranged, the point of highest position of the aero-foil section of the blade is situated 20~ generally directly opposite the tra~.lin~ edge o~ the precedi.ng vane.
Thus taking this area between the bl.acles that is from the trailing edge of one blade to the highest point of the next trailing blade, this area between the blades is
Tllis inverltion reLates to a ~luicl tnrbirle, more particularly to a wind turbine althougll ;t may a]so be clriven by other fluids such as water.
BACKGROUND OF THE rNVENTION
_ _ _ 5- Units for e~tracting the power from the wind have been known for centuries Eor driving mills, pumping water and the like. However these were very inefficient and had to be large in order to produce the required power.
ln- Of recent years turbines ha e been developed in order to achieve greater efficiency from smaller units. Australian Patent number 513,247 discloses a wind turbine assembly having a rotor with a plurality of vanes in radially spacecl relation to the axis, and flow controlling duct means to 15~ conduct a radial outflow of air against the vanes, the turbine havi-ng an aero-Eoil surface formecl on atl inlet duct, the vanes being situated in a low p~-ess~lre area at the trailing edge of the aero--foil.
Australian Patent AppL;cation number 213,391/77 cliscloses 20- a turbine rotor having vanes mountecl in a convergent-divergent duct, flow channels through the duct wal] controLling the boundary layer.
Australian Patent number 492,087 shows a wind turbine having a duct in which ls mounted stator and rotor blades.
25. It is an object of this invention to provide an improved willd turbine hav;ng advantages over the known art, in that ; it is more effective Ln converting the wind energy lnto motive power.
It is a further object to provide a wind turbine which is effective in delivering power from winds of low velocity.
.. , `~
SUMMARY OE l'llEi lNVEN'[`~ON
There is pro~ided according to the invention a fluid turbine to deliver power extracted from the fluid, a turbine havi.ng a rotor mounted ~or rotation about a axis parallel to 5- the flow, a plurality of vanes carri.ed by said rotor, a housing having in cross-section an aero-Eoil section, said vanes being situated in a passage through the aero-foil section at a position corresponding generally to the centre of lift of the aero-foil section whereby fl.uid flows from the high pressure 10. area to the low pressure area o~ the aero-foil section through the passage to thus act on the turbi.ne blades.
BRIEF DESCRIPTlON OF THE DRAWING~
Figure l i.s a perspective vi.ew of a turbine according to the invention.
15- Figure 2 is a cross-sectional view of the turbine.
Figure 3 is a d.iagramatic-sectional view of the invention.
Figure 4 is a diagramatic part-sectiona]. view of the vanes on the rotor, and Figure 5 is a perspective view of one vane.
20. DESCRIPTION OF T~IE PREE ERRED EMBODIMENT
Referring to the drawings tElere is shown a turbine 1 having a rotor 2 mounted on a shaft 3 supporting a bearing 4. Beari.ng 4.is supported on a frame 5, the turbine ~
being mounted on a shaft supported in a bearing 7. The ~5- drive from the turbine wheel 2 can in this embodiment be by a friction whee]. 8 attached to a drive shaft 9 which passes dowllwardly through the pedestal 6 and from which motive power may be obtained.
7~)8 The tnrbine wheel. 2 earrLes a plurality of vanes 10 to whi.ch are attflche(l a Eorwar(l fa:irl'llg ll.
The turbirle 1 also inc]udes a hollow aerodynamically shaped bod~ 12, a tai] portion 13 being prov:i.ded so that 5. the turbine unit will be qu;.ckl~ orientated into the pre-vai].ing air fiow~
Turning now to ~igure 3 the-re is shown a aero-foil ,section 14 having an upper surface 15, lower surface 16, ~~' leading edge 17 and trailing edge 18. As is known with lO. aero-foil sections, there is a reduced pressure formed over the upper surface and that there is an area or portion at which the centre of pressure is considered to act. If now it is considered that a duct or passage 19 is formed through the aero-foil section at the centre of pressure, that the air flow 15. forming Lhe reduced pressure above the aero-foil will cause a flow of fl~lid through the passage into the area of reduced pressure. This,~concept is utilised in the present invention and it wilL be seen that the fa:iring ll merges into the housing l2 to form an aero-foi]. shape, the fairing 11 being curved 20. in an aero~foil. section.
- .
The turbine wheel 2 is also provided with a conical deflecting surface 20 which also ;.s mounted on the shaft 3 and joins to the turbine wheel adjacent to the vanes The vanes 10 are attached to the turbine whee~ and 25. extend forwardly in cantilever fashion~ the vanes carryi.ng at their forward end the fairing 11 which thus rotates with the vanes. As shown in Figures ~ and 5 the vanes 10 are formed in this example of sheet metal with end flanges 21 by which the vanes are mounted on the turbine whee]
3~. 2 and to which the fairing is attached. It has been found that each of the vanes subtend an angle in the order of ~ , .
~3'78~8 8 to 16 degrees, but preEerabLy 12 clegrees and it is preferred that each vane of a cord length in the vicinity of lOOmm at least; for it is we11 known i.n the model aircraft art that this is the mir1imum cord ]ength wh:i.cil is required to achieve 5. satisfactory liLt and performance.
Each of the blades is shaped so that the leading edge is straight for approximately one third of its length along the line angle A-B, and similarly the trailing edge is straight for approximately one third of its length along lO. the line angle B-C.
The chord line A-C is preferably sltuated between 50 and 60 degrees but more particularly 56 degrees from the radial line, ancl the l.eadin~ edge angle A-B is situated between 30 and 40 degrees frorn the chord line, more 15. particularly 37 degrees, with the trailing edge line B-C being situated between 75 and 85 degrees, more parti.cularly 7 degrees from the radial line.
Wi.th the blades so arranged, the point of highest position of the aero-foil section of the blade is situated 20~ generally directly opposite the tra~.lin~ edge o~ the precedi.ng vane.
Thus taking this area between the bl.acles that is from the trailing edge of one blade to the highest point of the next trailing blade, this area between the blades is
2.5. approximately 2~ times Less than the inlet area, but considering the total. area of the l~l.ade exhaust around the circ~lmference of the turbine, this is equal to the inlet area.
In this way it was seen that the air flowing over the turbine unit creates a low pressure areaat the exhaust ~3'7~
6.
of the bl.ades, ancl thus the air :i.n passing through the blades into this low pressure area callses the turbine wheel to rotate.
In rotating, the nose fairing also rotates, and this 5~ rotation it is believed causes a :layer of air to trail or rotate with the inlet fairing thus causing a rotating mass of air which in effect extends the aero-foil shape of the fairing, and thus creates an aero-foil shape of greater depth which enhances the l.ow pressure area behind ~o. the rotating inlet fairing and so creates a greater low : pressure area into which the air will exhaust.
As the inlet area of the turbi.ne is equal to the exhaust area between the blades, there is no back pressure created, but in effect the opposi.te occurs due to the fact that the blades 1~. exhaust the air into the low pressure area of the aero--foil section.
It will be seen also that due to the positioning of the blades that the forces acti.ng orl the blades over the whoLe length of the blade are a]l acting at the same radius, 200 and the forces are thus tangential over the whole length of the blade at the maximum radius so that a greater turning e~fect is achieved.
Thus with the blades being mounted to extend generally parallel to the axis of the turbine, and with the blades 25. being formed in an aero-foil section, the chord line and the aero-foil section extellds generally i.n ~he direction o~ movement of the blade, that is generally tangentially to the turbine disc, but with the blade being inclined so that the leading edge is at a l.esser radius than the trailing eclge.
.
7.
In an al~ernclti.ve embocJiment, the inl.et Ea:iring may not be attached to the vanes, but maybe mounted on a spi.der or the like attached to the shaft, but in this embodiment the radia] attachments from the shaft to the fairing woul.d 5. interfere with the air flow, and also the advantage of the rotating inlet fairing wouLd not be achieved.
The turbine unit can be used for supplying any motive power either driving an electrical generator, hydraulic pump, or mechanically to any desired unit requiring a motive 10. power. For example an electrical generator or a hydraulic pump may be mounted dîrect]y or through gearing in the turbine housing itself.
The unit could be provided fo-~ pumping water in remote areas, providing electrical power to a direct power source 15. or for charging batteries or the like. For example it can be mounted on saili.ng craft, yachts and the :Li.ke to provide e]ectrical power for lighting, cooking and com-munications.
The unit would a]so operate i.n water and could be 20~ used in areas of flowing water such as streams with a gen-ration of power.
In this way it was seen that the air flowing over the turbine unit creates a low pressure areaat the exhaust ~3'7~
6.
of the bl.ades, ancl thus the air :i.n passing through the blades into this low pressure area callses the turbine wheel to rotate.
In rotating, the nose fairing also rotates, and this 5~ rotation it is believed causes a :layer of air to trail or rotate with the inlet fairing thus causing a rotating mass of air which in effect extends the aero-foil shape of the fairing, and thus creates an aero-foil shape of greater depth which enhances the l.ow pressure area behind ~o. the rotating inlet fairing and so creates a greater low : pressure area into which the air will exhaust.
As the inlet area of the turbi.ne is equal to the exhaust area between the blades, there is no back pressure created, but in effect the opposi.te occurs due to the fact that the blades 1~. exhaust the air into the low pressure area of the aero--foil section.
It will be seen also that due to the positioning of the blades that the forces acti.ng orl the blades over the whoLe length of the blade are a]l acting at the same radius, 200 and the forces are thus tangential over the whole length of the blade at the maximum radius so that a greater turning e~fect is achieved.
Thus with the blades being mounted to extend generally parallel to the axis of the turbine, and with the blades 25. being formed in an aero-foil section, the chord line and the aero-foil section extellds generally i.n ~he direction o~ movement of the blade, that is generally tangentially to the turbine disc, but with the blade being inclined so that the leading edge is at a l.esser radius than the trailing eclge.
.
7.
In an al~ernclti.ve embocJiment, the inl.et Ea:iring may not be attached to the vanes, but maybe mounted on a spi.der or the like attached to the shaft, but in this embodiment the radia] attachments from the shaft to the fairing woul.d 5. interfere with the air flow, and also the advantage of the rotating inlet fairing wouLd not be achieved.
The turbine unit can be used for supplying any motive power either driving an electrical generator, hydraulic pump, or mechanically to any desired unit requiring a motive 10. power. For example an electrical generator or a hydraulic pump may be mounted dîrect]y or through gearing in the turbine housing itself.
The unit could be provided fo-~ pumping water in remote areas, providing electrical power to a direct power source 15. or for charging batteries or the like. For example it can be mounted on saili.ng craft, yachts and the :Li.ke to provide e]ectrical power for lighting, cooking and com-munications.
The unit would a]so operate i.n water and could be 20~ used in areas of flowing water such as streams with a gen-ration of power.
Claims (14)
THE EMBODIMENTS OF THE INVENTION IN WHICH AN EXCLUSIVE
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A fluid turbine unit to deliver power extracted from a moving fluid, the turbine having a turbine wheel mounted for rotation about an axis parallel to the fluid flow, a plurality of cantilever vanes mounted on said turbine wheel and extending to forward vane ends, an inlet fairing mounted for rotation adjacent the forward vane ends of said vanes, said inlet fairing having a cross-section which provides an aero-foil section such that fluid flowing over the outside of the inlet fairing is accelerated relative to the fluid flowing into the turbine, said vanes being situated in a passage through the aero-foil section at a position corresponding generally to the center of lift of the aero-foil section whereby the fluid flows through the passage to the lower pressure area of the aero-foil section to act on the turbine vanes.
2. A fluid turbine unit as defined in claim 1 wherein said vanes are of aero-foil shape each havings its chord line tangential to the turbine wheel.
3. A fluid turbine unit as defined in claim 2 wherein said turbine includes a housing extending rearwardly from said vanes, the housing forming a continuation of the aero-foil section, the vanes being attached at their forward vane ends to said inlet fairing, the inlet fairing rotating with the turbine wheel so that in operation the rotating fairing induces an enlarged artificial aero-foil section to increase the aero-foil affect on the moving fluid.
4. A fluid turbine unit as defined in any one of claims 1 to 3 wherein the fluid turbine unit is a wind turbine unit, the housing having a stabilising tail, and is mounted on a pedestal for rotation about a vertical axis.
9.
9.
5. A fluid turbine unit as defined in claim 3 where the vanes are formed of pressed metal each having a straight leading edge and a straight trailing edge the vanes being curved to aero-foil shape and positioned with the trailing edge of a leading vane opposite the high point of the next trailing vane to form a constricted passage with the outlet area of the vanes being of equal area to the inlet area of the turbine unit.
6. A fluid turbine unit as defined in claim 3 and including drive means to engage the turbine wheel, the drive means driving a shaft extending through the pedestal and coinciding with the said vertical axis.
7. A fluid turbine unit as set forth in claim 1, wherein said fluid turbine is a wind turbine unit and includes a housing having an aerodynamically shaped portion extending rearwardly from said vanes, each of said vanes has a leading edge and a trailing edge with respect to the direction of rotation about said axis and a chord line extending between said edges, said leading edge is spaced a lesser radial distance from said axis than said trailing edge, the chord line of each of said vanes subtends an angle in the range of from about 8° to about 16°, and said aero-dynamically shaped portion of said housing provides a continuation of said aero-foil section of said inlet fairing with said vanes being disposed at said aero-foil section adjacent the peripheral extent of the fairing and aerodynamically shaped portion of the housing.
8. A fluid turbine unit as set forth in claim 7, wherein said aero-foil section is substantially free of radial interruption by said vanes.
9. A fluid turbine as set forth in claim 7, wherein said chord line of each of said vanes subtends an angle 10 .
equal to 12° and each of said vanes has a chord length measured along the chord line of at least 100mm.
equal to 12° and each of said vanes has a chord length measured along the chord line of at least 100mm.
10. A fluid turbine as set forth in claim 7, wherein each of said vanes has a cross-section including a sub-stantially linear portion extending from each of the edges thereof and joining with a curved aero-foil intermediate portion.
11. A fluid turbine unit as set forth in claim 3, wherein said vanes include rearward ends, said rearward and forward ends comprising end flanges for respectively securing said vanes between said turbine wheel and inlet fairing.
12. A fluid turbine as set forth in claim 11, wherein each of said vanes has an aero-foil section provided by a sheet material extending between said end flanges.
13. A fluid turbine as set forth in claim 12, wherein said end flanges comprise integral extensions of said sheet material.
14. A fluid turbine as set forth in claim 13, wherein said sheet material is sheet metal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000401691A CA1187808A (en) | 1982-04-26 | 1982-04-26 | Turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000401691A CA1187808A (en) | 1982-04-26 | 1982-04-26 | Turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1187808A true CA1187808A (en) | 1985-05-28 |
Family
ID=4122660
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000401691A Expired CA1187808A (en) | 1982-04-26 | 1982-04-26 | Turbine |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA1187808A (en) |
-
1982
- 1982-04-26 CA CA000401691A patent/CA1187808A/en not_active Expired
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |