A TURBINE ASSEMBLY

Abstract

A turbine assembly for a generator including a rotor that is operable to rotate about an axis; and a thrust absorbing member, wherein fluid is operable to enter the turbine assembly generally axially with regard to the axis of rotation of the rotor and to exit the turbine generally radially with regard to the axis of rotation of the rotor. The fluid is operable to contact the thrust absorbing member prior to contacting the rotor.

Claims

1. A turbine assembly for a generator comprising: a. a rotor that is operable to rotate about an axis; and b. a thrust absorbing member, wherein fluid is operable to enter the turbine assembly generally axially with regard to the axis of rotation of the rotor and to exit the turbine generally radially with regard to the axis of rotation of the rotor; and wherein the fluid is operable to contact the thrust absorbing member prior to contacting the rotor.

2. The turbine assembly according to claim 1, wherein the turbine assembly is for low head pressure.

3. The turbine assembly according to claim 1, wherein the thrust absorbing member and rotor are coupled.

4. The turbine assembly according to claim 1, wherein the rotor is operable to rotate about a shaft.

5. The turbine assembly according to claim 1, wherein the thrust absorbing member is coupled to the shaft.

6. The turbine assembly according to claim 1, wherein the thrust absorbing member further comprises fluid directing blades or vanes.

7. The turbine assembly according to claim 6, wherein the fluid directing blades or vanes of the thrust absorbing member are operable to direct the fluid to move over the rotor generally radially with regard to the axis of rotation of the rotor.

8. The turbine assembly according to claim 6, wherein the fluid directing blades or vanes direct the fluid exiting the thrust absorbing member tangentially to an orientation of rotor blades or vanes adjacent to the thrust absorbing member.

9. The turbine assembly according to claim 6, wherein the fluid directing blades or vanes of the thrust absorbing member are curved oppositely to the curvature of the rotor blades or vanes.

10. The turbine assembly according to claim 6, wherein the fluid directing blades are fixedly attached to the thrust absorbing member or form a reversibly attachable fluid directing member.

11. The turbine assembly according to claim 1, wherein a ratio of the diameter of the thrust absorbing member to the diameter of the rotor is less than 1:2.

12. The turbine assembly according to claim 1, further comprising a turbine housing.

13. The turbine assembly, according to claim 1, wherein the thrust absorbing member is operable to be axially variable such that the thrust absorbing member is operable to optionally obstruct the flow of fluid entering the rotor.

14. An apparatus for use in a generator comprising: a. a turbine assembly comprising a rotor that is operable to rotate about an axis; b. a turbine assembly inlet channel; c. a turbine assembly bypass channel; and d. a pressure regulating member wherein fluid is operable to enter the turbine assembly from the inlet channel generally axially with regard to the axis of rotation of the rotor and to exit the turbine generally radially with regard to the axis of rotation of the rotor; wherein the inlet channel is operable to be in fluid communication with the bypass channel through a bypass aperture, wherein the pressure regulating member is operable to be moved from a first position to a second position, wherein in the second position the pressure regulating member restricts fluid flow through the bypass aperture to a greater extent than in the first position, and wherein fluid that enters the bypass channel is diverted from entering the turbine assembly through the inlet channel.

15. The apparatus according to claim 14 wherein in the second position the pressure regulating member extends over the bypass aperture to a greater extent than in the first position.

16. The apparatus according to claim 14, wherein the rotor comprises a fluid entrance aperture and wherein the pressure regulating member is operable to be moved from a first position to a second position, wherein in the second position the pressure regulating member restricts fluid flow through the entrance aperture to a greater extent than in the first position.

17. The apparatus according to claim 16, wherein in the second position the pressure regulating member extends over the fluid entrance aperture of the rotor to a greater extent than in the first position.

18. The apparatus according to claim 14, wherein the pressure regulating member is operable to move between the first and second positions in response to the pressure of the fluid entering the apparatus.

19. The apparatus according to claim 14, wherein the pressure regulating member is biased into the first position or second position.

20. The apparatus according to claim 14, wherein the pressure regulating member is biased by a spring.

21. The apparatus according to claim 14, wherein there is more than one bypass apertures, typically, more than two bypass apertures, such as more than live bypass apertures.

22. The apparatus according to claim 14, wherein the apparatus further comprises an inlet channel and wherein the pressure regulating member forms an inner sleeve of the inlet channel.

23. A generator comprising a turbine assembly according to claim 1 and/or an apparatus according to claim 14.

24. The generator according to any claim 23, wherein rotor further comprises magnets.

25. The generator according to claim 23, wherein the generator is an inlet generator, typically a swimming pool water inlet generator.

Description

BRIEF DESCRIPTION OF DRAWINGS

[0088] FIG. 1 shows a top view of a partially assembled turbine assembly of the present invention.

[0089] FIG. 2 shows a side view of the thrust absorbing member of FIG. 1.

[0090] FIG. 3 shows a side perspective view of the rotor of FIG. 1.

[0091] FIG. 4a shows a top view of the turbine assembly of FIG. 1 in a further assembled configuration.

[0092] FIG. 4b shows a side view of the turbine assembly of FIG. 4a.

[0093] FIG. 5 shows a side perspective view of a guide member.

[0094] FIG. 6 shows a side perspective view of the turbine assembly of FIG. 1 with the guide member of FIG. 5.

[0095] FIG. 7 shows a top view of the turbine assembly of FIG. 4a with the guide member of FIG. 5.

[0096] FIG. 8 shows a top view of the turbine assembly of FIG. 7 within a turbine housing.

[0097] FIG. 9 shows a cross-sectional side view of a turbine assembly according to the present invention.

[0098] FIG. 10 shows a side cross-sectional side view of a turbine assembly according to the present invention.

[0099] FIG. 11 shows expanded cross-sectional side view of a thrust absorbing member of a turbine assembly according to the present invention.

[0100] FIG. 12 shows a cross-sectional side view of a turbine assembly according to the present invention.

[0101] FIG. 13 shows a cross-sectional side view of a non flush pool inlet light.

[0102] FIG. 14 shows a cross-sectional side view of a flush pool inlet light.

DESCRIPTION OF EMBODIMENTS

[0103] Referring first to FIG. 1, there is shown a turbine assembly 100 of the present invention. Turbine assembly 100 is formed of rotor 140 and thrust absorbing member 120.

[0104] Rotor 140 is circular in shape, forming a disk. Rotor 140 is operable to rotate about a central axis. Rotor 140 has aperture 122 at its centre. FIG. 1 views turbine down the central axis which is marked with (X).

[0105] Thrust absorbing member 120 has a circular lower edge that has a diameter smaller than the diameter of rotor 140.

[0106] Thrust absorbing member 120 is positioned on the at the centre of the top surface of rotor 140, on the central axis. Rotor 140 extends laterally beyond thrust absorbing member 120 and an outer ring of rotor 140 is exposed, on which blades 142 are positioned. Rotor 140 contains six blades 142.

[0107] Rotor 140 is formed of a rotor base 141 and blades 142 that extend from rotor base 141. Blades 142 are raised section of rotor 140. Blades 142 are positioned from inner edge of exposed rotor 140, adjacent to thrust absorbing member 120, and are orientated in a spiral manner towards the outer edge. The orientation of the spiral blades 142 dictate whether the rotor will rotate clockwise or counter clockwise about its central axis in use. Rotor 140 in FIG. 1 is shown with blades 142 that are orientated so that they spiral outwards in a clockwise manner, and therefore, will induce a counter clockwise rotation of the rotor in use.

[0108] Thrust absorbing member 120 of FIG. 1 is shown from a side view in FIG. 2. Thrust absorbing member 120 has a circular cross section and forms a rounded cone like shape. The apex of thrust absorbing member 120 is centred on the central axis of rotor 140 in use. The lower edge of thrust absorbing member 120 is flared outwardly at the edges. Thrust absorbing member 120 is fixedly attached to shaft 126. Fixed shaft 126 is positioned along the central axis of thrust absorbing member 120. Thrust absorbing member 120 is partially hollow and shaft 126 is fixed at one end at the centre of the inside portion of thrust absorbing member 120.

[0109] The outside portion of thrust absorbing member 120 is the surface that contacts the fluid in use. The shape of the outside portion of the thrust absorbing member 120 is a convex bell shape as seen in FIG. 2.

[0110] Shaft 126 extends below thrust absorbing member 120 and through bearing 124. In turbine assembly 100, thrust absorbing member 120 is independently coupled to rotor 140 by shaft 126 that goes through the aperture of rotor 122, thereby through the central axis of rotor 140, labelled (X).

[0111] Aperture 122 of rotor 140 is configured to accept bearing 124, allowing free rotation about shaft 126 that is connected to thrust absorbing member 120. The upper face of rotor 140 is depressed in the centre where the thrust absorbing member is positioned in turbine assembly 100. The depression is circular and is only slightly larger than the periphery of the lower edge of thrust absorbing member 120 so that the thrust absorbing member 120 forms a close fit within the depression. This factor, combined with the depth of the depression and the height of the base of the lower edge of the thrust absorbing member results in the outer face of the flared base of thruster absorbing member 120 being generally flush with the outer face of rotor 140 when assembled as seen in FIG. 1.

[0112] Thrust bearing 125 facilitates the rotation of rotor 140 about shaft 126. In use fluid enters the turbine assembly and passes over thrust absorbing member 120 which absorbs the force from the fluid flow and minimises its distribution so that little to no axial force is transferred to thrust bearing 125.

[0113] In one example (not shown) thrust absorbing member 120 is raised slightly in the axial direction relative to rotor 140 to enhance flow of fluid between thrust absorbing member and rotor.

[0114] Rotor 140 also contains connecting members 146 that are formed as part of blades 142. Connecting members 146 are raised nodules on the top surface of blades 146 that reversibly attach rotor base 141 with a capping member 150. Turbine assembly 100 is shown with rotor 140 and capping member 150 in FIGS. 4a and 4b.

[0115] Capping member 150 and rotor base 141 is concentric and coterminal. Accordingly, capping member 150 is circular disk that has the same diameter as rotor 140. Capping member 150 provides a ceiling for forming flow channels in turbine assembly 100. Flow channels 148 are delineated at the bottom by fluid contacting surface of rotor 140, the sides by blades 142 and the top by capping member 150. Flow channels 148 are thereby between adjacent blades 142 of rotor 140. As shown in FIG. 3, the turbine assembly has six blades and therefore six flow channels. Flow channels 148 have an inner opening, where fluid enters, which is adjacent to thrust absorbing member 120, and an outer opening, where fluid exits, which is at the outer edge of rotor 140 (seen in FIG. 4b).

[0116] Capping member 150 contains a large central aperture, which is the same diameter as the maximum diameter of thrust absorbing member 120. When assembled, the central apex of thrust absorbing member 120 extends through the central aperture of capping member 150. The gap between the central aperture of capping member 150 and thrust absorbing member 120 forms fluid entry point 180 of turbine assembly 100, this is the axial inflow of the turbine assembly.

[0117] Capping member 150 contains multiple smaller apertures that are complementary in size and position to connecting members 146. Connecting members 146 couple with apertures in capping member 150 to connect rotor 140 with capping member 150, thereby forming channels 148. Alternatively, capping member 150 and rotor 140 may be fixedly attached (not shown).

[0118] Fluid directing blades 162 optimise the angle of the fluid as it passes over thrust absorbing member 120, thereby further directing fluid entering flow channels 148 from thrust absorbing member 120. Fluid directing blades 162 spiral from the central surface of thrust absorbing member 120 to its outer edge in a different pattern to the blades 142 of rotor 140. Accordingly, if rotor blades 142 of rotor 140 spiral clockwise, fluid directing blades will spiral counter-clockwise, and vice versa. Fluid directing blades 162 are curved blades that have outer edges that are complementary in shape to the outer face of thrust absorbing member 120. This allows for fluid directing blades 162 to be flush to thrust absorbing member 120.

[0119] Fluid directing blades 162 optimise the fluid over the thrust absorbing member so that on entry to rotor 140 the fluid strikes blades 142 perpendicularly, thereby producing a highly efficient turbine assembly. Further, this arrangement results in thrust absorbing member 120 advantageously absorbing further force axial thrust from the incoming fluid in turbine assembly 100.

[0120] Fluid directing blades 162 may be fixedly attached to thrust absorbing member 120 (not shown). Fluid directing blades 162 are fixedly attached to ring 166 to form fluid directing member 160, as shown in FIG. 5.

[0121] Ring 166 of fluid directing member 160 is formed about central aperture 164. Ring 166 is formed of main inner ring 167, which is expanded at the top to form outer ring 168. The diameter of inner ring 167 is the same, or slightly smaller, than thrust absorbing member 120, and therefore central aperture of capping member 150. When assembled, inner ring 167 engages the complementary central aperture of capping member 150; outside ring 168 is larger than the central aperture and secures fluid directing member 160; and fluid directing blades 162 are flush with the surface of thrust absorbing member 120.

[0122] Turbine assembly 100 is shown in FIG. 6 formed of rotor 140, thrust absorbing member 120 and fluid directing member 160 so that the orientation of fluid directing blades 162 and blades 142 of rotor 140 is visible.

[0123] In use, fluid enters turbine assembly 100 along the central axis (X) of rotor 140, about which it rotates, and hits thrust absorbing member 120. Some of the axial force of the input fluid is absorbed, and the fluid is deflected by thrust absorbing member 120 to move generally radially with regard to the axis of rotation of rotor 140, over rotor 140 and into blades 142, turning rotor 140.

[0124] FIG. 7 shows a top view of turbine assembly 100 formed of rotor (not shown), thrust absorbing member 120, capping member 150 and fluid directing member 160. From the top view apertures can be seen that are formed by outer ring 168 and fluid directing blades 162 of fluid directing member 160, and thrust absorbing member 120. These apertures are fluid entry points 180 of turbine assembly 100.

[0125] Turbine assembly 100 may be fixed to turbine housing 190. Turbine housing 190 is a complementary casing that attaches to turbine assembly 100 and allows rotor 140 to rotate in use. Turbine housing 190 provides an interface for a fluid pipe that can be attached at attachment points 192, which are positioned in a circle around turbine assembly 100 for use with a pipe with a circular cross section, thereby sealing turbine assembly 100 at the end of a fluid inlet pipe, for example, a water inlet pipe. Thrust absorbing member 120 is positioned at the centre of attachment points 192, and fluid entry points 180 allows fluid to enter turbine assembly 100 from a fluid inlet pipe (not shown) that is attached to turbine housing 190.

[0126] FIG. 9 shows a cross-sectional side view of turbine assembly 100 formed of rotor 140, capping member 150, thrust absorbing member 120, shaft 126 and fluid directing member 160. The side view of turbine assembly 100 has the shaft aligned vertically, along the axial axis, with the fluid inlet arranged at the top of the turbine assembly. The fluid flow through turbine assembly 100 is indicated by the dashed arrows. Fluid enters the turbine assembly inlet and passes over thrust absorbing member 120 and enters rotor 140 via the junction 210 which is the border between rotor 140 and thrust absorbing member 120. Junction 210 represents the thrust absorbing member 120 fluid outlet and the rotor 140 fluid inlet. Fluid then passes through rotor 140 and exits turbine assembly 100.

[0127] Thrust absorbing member 120 is fixedly attached to shaft 126 which is moveable in the axial direction as indicated by the double headed arrows in FIG. 9. Rotor 140 is free to rotate on shaft 126. In other words. thrust absorbing member 120 and shaft 126 are fixed together and can be moved axially by moving shaft 126 to alter the size of junction 210 between thrust absorbing member 120 and rotor 140. In one example, shaft 126 is only moveably in an axial direction.

[0128] Thrust absorbing member 120 is shown in a first open configuration in FIG. 9 when thrust absorbing member 120 is flush with rotor 140 allowing fluid to flow out of the thrust absorbing member outlet and into the rotor inlet at junction 210.

[0129] In use, when shaft 126 is moved towards the fluid inlet, the exit aperture from thrust absorbing member 120 can be moved from an open configuration to a closed configuration.

[0130] Thrust absorbing member 120 may be moveable axially independently of shaft 126 as shown in FIG. 10. FIG. 10 shows a cross-sectional side view of turbine assembly 100 as described in FIG. 9, however, thrust absorbing member 120 is fixed to shaft 126 by biasing means 220. In the embodiment shown in FIG. 10, shaft 126 is fixed with rotor 140 free to rotate about shaft 126 and thrust absorbing member 120 is rotationally fixed to shaft 126 but can move in an axial direction on shaft 126, for example, against a biasing means 220. In other words, thrust absorbing member 120 can move axially independent of shaft 126. Thrust absorbing member 120 can be extended or retracted along coinciding axes of shaft 126 by a telescopic action.

[0131] In FIG. 9, an axially movable shaft is connected to a thrust absorbing member to regulate flow into the rotor. An alternative arrangement could be adopted whereby torque from the rotor could be transferred to an alternative generator assembly (not shown), such as an alternative generator assembly that is not integral to the rotor or adjacent housing. The axially moveable shaft connected to the thrust absorbing member may then pass through the drive shaft centre. Thus, the drive shaft would rotate around an axially moveable shaft. The two shafts could alternatively rotate together.

[0132] In a further embodiment of the assembly of FIG. 9, a sealed cavity could be present beneath the thrust absorbing member 120, such as by providing seals between the thrust absorbing member 120 and rotor 140. Fluid may be operable to enter and exit the sealed cavity, such as via the shaft 126, such as to allow for hydraulic movement of the thrust absorbing member. Such a configuration may allow for improved control of the movement of the thrust absorbing member.

[0133] Turbine assembly 100 in FIG. 10 is shown in a second closed configuration wherein thrust absorbing member 120 is extended into the turbine inlet and prevents fluid from entering rotor 140.

[0134] In the closed configuration, the outer edges of thrust absorbing member 120 are adjacent to the fluid directing member 160 and turbine housing 190 such that fluid is prevented from entering rotor 140.

[0135] Thrust absorbing member 120 in FIG. 10 is extended and elongated along the axial axes of turbine assembly 100 against biasing means 220. In one example, biasing means 220 is a compression spring. As fluid enters turbine assembly 100, it creates a force upon thrust absorbing member 100 which is transferred to shaft 126 via biasing means 220. As the pressure in the fluid inlet increased biasing means 126 may be compressed by the force of the fluid and this force acts on biasing means 220 causing compression. Therefore, as the pressure increases, biasing means 220 compresses and results in thrust absorbing member 120 retracting onto shaft 126, thereby aligning the outlet of thrust absorbing member 120 with the inlet into rotor 140 at junction 210 resulting in the turbine assembly changing to a first open configuration where fluid can enter rotor 140.

[0136] In use, the flow of the fluid entering turbine assembly 100 applies force onto thrust absorbing member 120 which moves due to compression of biasing means 220, thereby increasing the outlet of the thrust absorbing member (i.e. increasing its exit aperture) from a closed to an open configuration. It is also understood that depending on the flow rate, the force applied to the turbine assembly may result in the biasing means being partially compressed and therefore, the fluid exiting thrust absorbing member 120 and entering rotor 140 via junction 220 is partially restricted. In other words, the amount of fluid entering rotor 140 is self-regulated by turbine assembly 100.

[0137] FIG. 10 shows an arrangement whereby the thrust absorbing member 120 progressively moves towards the rotor 140 in response to an increased inlet flow pressure. This arrangement may additionally allow for a check on flow direction, meaning that if a suction flow is applied to the rotor assembly inlet port, the fluid flow would enter on the periphery of the rotor. As such the flow would enter the rotor radially inwards and then exit axially under a negative pressure. The thrust absorbing member under this reverse flow condition (for example if the device is connected inappropriately to a suction port on a circulation system) would ‘check’ the flow closing the water passages between the thrust absorbing member and rotor at 210.

[0138] FIG. 11 shows a cross-sectional expanded side view of turbine assembly 100. The fluid flow through is indicated by the dashed arrows. Thrust absorbing member 120 comprises integral guide vanes 224 which can be considered as male components. In use, thrust absorbing member 120 is operable to move upwards towards the fluid entry point 180 and associated guide ring 226, and retract, as indicated by the double headed arrows. In other words, FIG. 11 shows a telescopic guide vane assembly.

[0139] When thrust absorbing member 120 is aligned with letter A as shown in FIG. 11, the junction 210 is open so that fluid flow between thrust absorbing member 120 and rotor (not shown). As thrust absorbing member 120 moves to a closed configuration (i.e. towards point B) the aperture between thrust absorbing member 120 and rotor (not shown) is closed so that junction 210 no longer connects thrust absorbing member 120 and rotor (not shown).

[0140] Guide ring 226 contains slots to accept guide vanes 224 of thrust absorbing member 120 as thrust absorbing member 120 moves from A towards B. In other words, associated guide ring 226 is female and accepts thrust absorbing member guide vanes 224 in a telescopic action (male—female). In one example, guide ring 226 may be part of the housing 190 as shown in FIG. 10.

[0141] FIG. 12 shows a cross-sectional side view of an alternative embodiment according to the present invention in which turbine assembly 100 is formed of thrust absorbing member 120, shaft 126, rotor 140 and capping member 150. Thrust absorbing member 120 is fixedly attached to shaft 126, with rotor 140 and capping member 150 free to rotate about shaft 126. Bypass arrangement 230 is positioned between thrust absorbing member 120 and inlet and provides an adjustable inlet to bypass fluid channel 242.

[0142] Bypass arrangement 230 is formed of inner sleeve 232, outer sleeve 236 and biasing means 240. Inner sleeve 232 contains inner aperture 234 and outer sleeve 236 contains outer aperture 238. Inner sleeve 232 is operable to move axially with respect to turbine assembly 100. Biasing means 240 biases bypass arrangement 230 into a closed configuration wherein inner aperture 234 and outer aperture 238 are not aligned and fluid cannot enter bypass fluid channel 242. In an open configuration the inner aperture 234 and outer aperture 238 are aligned. In use, the force of fluid entering turbine assembly 100 applies force onto outer sleeve 232 which if high enough, results in compressing biasing means 240 and moving inner sleeve 232 with respect to outer sleeve 236 and aligning or at least partially aligning inner aperture 234 and outer aperture 238 providing the fluid entering turbine assembly 100 flow through the bypass arrangement 230 into bypass fluid channels 242.

[0143] Inner sleeve 232 also acts to control the fluid exiting thrust absorbing member 120 and entering rotor 140 via junction 210. In bypass arrangement 230, when moving from an open to closed configuration, inner sleeve 232 moves in the axial direction providing the means to align or block the outer aperture 238 to bypass fluid channel 242. Additionally, inner sleeve 232 also acts to control junction 210 and can move axially so that junction 210 is in an open configuration and unobstructed, to a closed configuration when junction 210 is obstructed by inner sleeve 232 preventing fluid from entering rotor 140.

[0144] Inner sleeve 232 is positioned such that when biasing means 240 is expanded and bypass arrangement 230 is in a closed configuration, junction 210 is in an open configuration and fluid entering turbine assembly 100 is diverted by thrust absorbing member 120 and enters rotor 140 via open junction 120 (as shown in FIG. 12). When biasing means 240 is compressed, inner sleeve 232 is positioned such that bypass arrangement 230 is in an open configuration with inner aperture 234 and outer aperture 238 aligned, and inner sleeve 232 is blocking junction 210 and fluid entering turbine assembly 100 is prevented from entering rotor 140 due to closed junction 210 and is diverted to bypass fluid channel 242 by the open bypass arrangement 230 (not shown).

[0145] Biasing means 240 of bypass arrangement 230 is a piston device. In use, bypass arrangement 230 provides regulation means whereby movement of biasing means 240 piston due to excess flow moves the piston from an expanded state as shown in FIG. 12 (with the thrust absorbing member exit aperture fully open) to a compressed state (not shown) were the thrust absorbing member exit aperture closes and at the same time proportionally opening the bypass gate. When movement against spring pressure of biasing means 240 occurs the exit aperture is closed when the bypass arrangement fully open. This results in preventing excess flow and pressure from striking the rotor and provides a self-regulating method of the rotor speed.

[0146] A bypass arrangement may be positioned between turbine housing 190 and fluid inlet pipe (not shown) via attachment points 192 as shown in FIG. 9, to further regulate the fluid entering the turbine assembly, and therefore further optimise the efficiency of turbine assembly 100.

[0147] FIG. 13 shows an embodiment according to the present invention of a non-flush pool inlet light which is formed of thrust absorbing member 120, shaft 126, rotor 140 and capping member 150. Magnets 260 are fixedly attached to rotor 140 and are operable to generate power from the rotation energy of rotor 140. LED Light 262 is operable to be powered by the electricity generated by the rotation of rotor 140 and magnets 260.

[0148] FIG. 14 shows an embodiment according to the present invention of a flush fitting pool inlet light which is formed of thrust absorbing member 120, shaft 126, rotor 140 and capping member 150. Magnets 260 are fixedly attached to rotor 140 and are operable to generate power from the rotational energy of rotor 140. LED light 262 is operable to be powered by the electricity generated by rotation of rotor 140 and magnets 260. It is also shown a bypass arrangement 230 that provides a bypass flow for fluid entering the device that is considered too high flow. Bypass arrangement 230 is a spring-loaded bypass arrangement.

[0149] It is understood that the movement of the components in turbine assembly is relative to other components, accordingly it is understood that moving component A to B is equivalent of moving all other components from B to A. In other words, in a two-component system, either component can be designed to move when the other is fixed as shown throughout the figures.

[0150] It is understood that the turbine assembly described herein may be functional in any orientation. For consistency, the figures have generally shown the turbine assemblies with the flow inlet at the top and radial outlets at the sides, with the axial plane aligning with the vertical plane of the figures (y-axis). In other words, the turbine assembly and apparatus described herein are multi-orientational.

[0151] Attention is directed to all papers and documents which are filed concurrently with or previous to this specification in connection with this application and which are open to public inspection with this specification, and the contents of all such papers and documents are incorporated herein by reference.

[0152] All of the features disclosed in this specification (including any accompanying claims, abstract and drawings), and/or all of the steps of any method or process so disclosed, may be combined in any combination, except combinations where at least some of such features and/or steps are mutually exclusive.

[0153] Each feature disclosed in this specification (including any accompanying claims, abstract and drawings) may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. Thus, unless expressly stated otherwise, each feature disclosed is one example only of a generic series of equivalent or similar features.

[0154] The invention is not restricted to the details of the foregoing embodiment(s). The invention extends to any novel one, or any novel combination, of the features disclosed in this specification (including any accompanying claims, abstract and drawings), or to any novel one, or any novel combination, of the steps of any method or process so disclosed.