NL2014472B1

NL2014472B1 - Reaction turbine.

Info

Publication number: NL2014472B1
Application number: NL2014472A
Authority: NL
Inventors: Leegwater Rob
Original assignee: Arno Leegwater
Priority date: 2015-03-17
Filing date: 2015-03-17
Publication date: 2017-01-13
Also published as: NL2014472A

Abstract

The invention relates to a reaction turbine comprising a reaction chamber with a rotor assembly that is supported on the rotation shaft, wherein the rotor assembly comprises a first rotor with acceleration sections for receiving liquid and for centrifugally accelerating the liquid to form vapor cavities in the liquid, wherein each acceleration section comprises a curved acceleration channel, an implosion chamber and a thrust nozzle, wherein the implosion that in use chamber deflects is provided with the accelerated an impact surface liquid towards the thrust nozzle while the cavities in the liquid implode and causes shockwaves in the liquid, wherein the thrust nozzle is arranged for directing the shockwaves of liquid out of the first rotor in a thrust direction intersecting with a 15 first reaction element, causing an opposite reaction force that is exerted on the first rotor and thereby promoting rotation of the first rotor.

Description

Reaction turbine BACKGROUND

The invention relates to provide a reaction turbine, in particular a hydrodynamic cavitation reaction turbine, for generating useful work, e.g. in the form of mechanical energy or heat.

Hydrodynamic cavitation reaction turbines are known, for example from US 2004/0062647 Al, which discloses a rotodynamic fluidic system. This known system requires a considerable mechanical energy input to obtain and maintain cavitation. Furthermore, the rotors of said known reaction turbines rapidly wear out as a result of the cavitation, and thus require regular maintenance and costly replacement parts. The operational costs of running such a reaction turbine are relatively high. Therefore, small scale applications, e.g. for powering household appliances or as a compact boiler, have not been viable as of yet.

It is an object of the present invention to provide an alternative reaction turbine in which the efficiency of the energy output with respect to the energy input is increased and/or to reduce the operational costs of the reaction turbine.

SUMMARY OF THE INVENTION

The invention provides a reaction turbine comprising a housing with a cylindrical circumferential inner wall defining a reaction chamber with an inner volume which in use contains a liquid that is circulated through the reaction turbine, wherein the reaction turbine is provided with a rotation shaft extending concentrically with respect to the circumferential inner wall through the reaction chamber and defining a rotational axis of the reaction turbine, wherein the reaction turbine further comprises a rotor assembly that is supported on the rotation shaft in the reaction chamber to be rotatable about the rotational axis in a first rotational direction, wherein the rotor assembly comprises a first rotor with a plurality of acceleration sections for receiving liquid at or near the rotation shaft and for centrifugally accelerating the liquid towards the radial outside of the first rotor with respect to the rotational axis to form vapor cavities in the liquid, wherein each acceleration section comprises a curved acceleration channel that promotes the centrifugal acceleration, an implosion chamber in fluid communication with and downstream of the acceleration channel at or near the radial outside of the first rotor with respect to the rotational axis, and a thrust nozzle in fluid communication with and downstream of the implosion chamber, wherein the implosion chamber is provided with an impact surface that in use deflects the accelerated liquid from the acceleration channel towards the thrust nozzle while the cavities in the liquid implode and causes shockwaves in the liquid, wherein the thrust nozzle is arranged for directing the shockwaves of liquid out of the first rotor in a thrust direction, wherein the reaction turbine comprises a first reaction element that is arranged directly adjacent to the first rotor in the axial direction of the rotational axis, wherein the thrust direction is oriented towards or in a second rotational direction opposite to the first rotational direction and wherein the thrust direction intersects with the first reaction element, wherein the liquid in use impacts the first reaction element and causes an opposite reaction force that is exerted on the first rotor thereby promoting rotation of the first rotor in the first rotational direction.

The first reaction ring directly opposite to the thrust nozzle can improve and/or optimize the reaction forces being generated on the first rotor in the first rotational direction as the liquid impacts the first reaction ring in the second rotational direction, thereby improving the efficiency of the reactor turbine.

In an embodiment the acceleration sections are evenly distributed in the circumferential direction of the first rotor with respect to the rotational axis. The even distribution of the acceleration sections improves the uniformity of the overall forces exerted on the first reaction ring and the first rotor, thereby improving the consistency of the rotation of the first rotor in the first rotational direction.

In an embodiment each acceleration section comprises a collection chamber at or near the rotation shaft, in fluid communication with and upstream of the acceleration channel, wherein the collection chamber is arranged for collecting a volume of liquid prior to the liquid entering the acceleration channel. By collecting a considerable volume of liquid, the pressure and centrifugal force exerted by said liquid and the liquid in the acceleration channel can be increased, thereby improving the efficiency of the reactor turbine.

In an embodiment the reaction chamber comprises a centripetal section directly adjacent to the first reaction element at the side thereof facing away from the first rotor, wherein the centripetal section is arranged for receiving the liquid from the thrust nozzles of the respective acceleration sections and for forcing the liquid into a centripetal motion towards the rotation shaft. Preferably the centripetal section comprises a first cone having a conical surface that tapers towards the first rotor for forcing the liquid from the first rotor into a laminar centripetal flow towards the rotation shaft. The centripetal motion of the liquid can reduce the pressure exerted by the liquid on the circumferential inner wall, thereby reducing the friction of the liquid with respect to said circumferential inner wall such that the liquid and the rotor assembly rotating within said liquid can be rotated more easily.

In an embodiment the reaction chamber further comprises an evacuation section on the opposite side of the first cone with respect to the first rotor, wherein the first cone is provided with an escape port at or near the rotation shaft for allowing the centripetally inwardly moving liquid to flow from the centripetal section into the evacuation section. The evacuation section can be used to return the liquid to the rotor for renewed circulation of the liquid through the rotor.

In an embodiment the reaction turbine comprises a return conduit for returning the liquid that is received from the thrust nozzles of the respective acceleration sections to the first rotor. Preferably, the return conduit is provided with a first end that is in fluid communication with the evacuation section for receiving the liquid from said evacuation section. The return conduit can effectively guide the liquid from the evacuation section back to the first rotor.

In an embodiment the reaction turbine comprises a separation wall dividing the inner volume of the reaction turbine into the reaction chamber and a storage compartment, wherein the return conduit is provided with a second end that is in fluid communication with the storage compartment for returning the liquid from the reaction chamber to the storage compartment, wherein the storage compartment is in fluid communication with the first rotor for supply the returned liquid to the first rotor. The storage compartment can hold the returned liquid separately from the liquid in the reaction chamber and can prepare the returned liquid for renewed circulation through the first rotor into the reaction chamber.

In an embodiment the rotation shaft extends through both the reaction chamber and the storage compartment, wherein the rotation shaft is provided with a duct that is in fluid communication with the storage compartment and the first rotor for connecting the storage compartment in fluid communication to the first rotor. Thus, the rotation shaft can be used as a central duct for transferring the liquid from the storage compartment to the first rotor.

In an embodiment the first rotor is rotationally fixedly mounted to the rotation shaft so as to be rotatable together with the rotation shaft in the first rotational direction, wherein the rotation shaft is provided with a plurality of discharge ports connecting the duct in fluid communication with the respective acceleration sections in the first rotor. The discharge ports can be arranged in a fixed relative position with respect to the first rotor that is fixedly mounted to the rotation shaft, thereby ensuring a reliable transfer of the liquid.

In an embodiment the reaction turbine is provided with a plurality of discs rotationally fixedly mounted to the rotation shaft in the storage compartment to be rotatable together with the rotation shaft in the first rotational direction, wherein the plurality of discs is arranged for promoting a boundary layer effect in the liquid in the storage compartment with respect to the rotational axis. In this manner, the liquid can be given a smooth, non-turbulent rotation prior to the liquid entering the first rotor again.

In an embodiment the plurality of discs in use force the liquid to flow in a centripetally inward movement with respect to the rotational axis, wherein each of the plurality of discs is provided with a radially inner flow opening for allowing the centripetally inwardly moving liquid to flow along the rotation shaft towards the location where the storage compartment is in fluid communication with the reaction chamber. The centripetal motion of the liquid can reduce the pressure exerted by the liquid on the circumferential inner wall, thereby reducing the friction of the liquid with respect to said circumferential inner wall such that the liquid and the plurality of discs rotating within said liquid can be rotated more easily. In combination with the duct in the rotation shaft, the liquid can be efficiently sucked into the duct as a result of underpressure in the acceleration channels, thereby promoting the circulation of the liquid.

In an embodiment the reactor turbine further comprises a hydraulic accumulator that is arranged in fluid communication with the storage compartment for regulating the pressure of the liquid within the inner volume of the reactor turbine. By regulating the pressure of the liquid, the threshold for cavitation in the liquid can be adjusted. Thus the amount of cavitation can be controlled, thereby controlling the reaction force and thus the rotational velocity of the rotor assembly.

In an embodiment the return conduit is provided with at least one vortex chamber for manipulating the liquid to flow in a centripetal motion through the return conduit. Similar to the centripetal motion of the liquid in the inner volume of the reaction turbine, the centripetal motion of the liquid in the return conduit can significantly decrease the amount of friction between the liquid and the return conduit.

In an embodiment the return conduit is double walled, wherein the double wall in use is filled with a coolant medium to control the temperature of the liquid flowing through the return conduit. In this manner, the reaction turbine can be kept from overheating.

In an embodiment the first reaction element is provided with a plurality of reaction holes for promoting the reaction force of the liquid with respect to the first rotor. The reaction holes can be suitably optimized to obstruct the flow of the liquid in the thrust direction and to maximize or to generate an optimal reaction surface for the liquid, resulting in an oppositely oriented reaction force on the first rotor.

In an embodiment the first rotor comprises a replaceable maintenance part, wherein at least the impact surface and preferably also the implosion chamber is located within the maintenance part. The maintenance part, or at least the impact surface in the maintenance part, can be easily replaced by a new one when worn out by the cavitation. Alternatively, the element containing the impact surface can be replaced by another element having a different impact surface, suiting different operating conditions and/or different liquid characteristics.

In an embodiment the reaction turbine comprises a second rotor and a second reaction element which are functionally similar, equivalent or identical to the first rotor and the first reaction element, respectively, wherein the second rotor and the second reaction element are placed at a distance from the first rotor and the first reaction element in the axial direction of the rotational axis. The second rotor and second reaction element can increase or even double the reaction forces being exerted on the rotor assembly, thereby increasing the amount of useful work that can be extracted from the rotation of the rotor assembly in the first rotational direction.

In a preferred embodiment thereof the second rotor and the second reaction element are mirror symmetrical to the first rotor and the first reaction element in a plane perpendicular to the rotational axis, wherein the centripetal section is located between the first reaction element and the second reaction element in the axial direction of the rotational axis. Both rotors can thus discharge liquid via the respective reaction elements into the same centripetal section.

In an embodiment the centripetal section comprises a second cone having a conical surface that tapers towards the second rotor for forcing the liquid from the second rotor into a laminar centripetal flow towards the rotation shaft. Similar to the first cone, the centripetal motion of the liquid caused by the second cone can reduce the friction of the liquid with respect to the inner circumferential wall.

In an embodiment the evacuation section is located between the first cone and the second cone in the axial direction of the rotational axis. The liquid that moves centripetally inwards from both rotors can thus be evacuated through the same evacuation section.

In an embodiment the inner volume of the reaction turbine comprises the aforementioned liquid, preferably of the group comprising water, liquid carbon dioxide (R744) or an emulsion of two or more liquids, preferably an emulsion of water and oil. In particular liquid carbon dioxide has been known to cause considerable expansion when changing phase from the liquid phase to gaseous phase, thereby considerably improving the acceleration, the centrifugal forces, the cavitation, the intensity of the resulting shockwaves upon imploding and the reaction forces. Hence, the overall efficiency of the reaction turbine can be greatly improved.

The various aspects and features described and shown in the specification can be applied, individually, wherever possible. These individual aspects, in particular the aspects and features described in the attached dependent claims, can be made subject of divisional patent applications .

BRIEF DESCRIPTION OF THE DRAWINGS

The invention will be elucidated on the basis of an exemplary embodiment shown in the attached schematic drawings, in which: figure 1 shows an isometric view of a hydrodynamic cavitation reaction turbine according to the invention; figure 2 shows a side view of the reaction turbine according to figure 1; figure 3 shows a side view in cross section of the reaction turbine according to the line III - III in figure 1; figure 4 shows an isometric exploded view of the internal components of the reaction turbine according to figures 1-3, including a rotor assembly; figure 5 shows a front view in cross section of the rotor assembly according to the line V - V in figure 2; figure 6 shows a detail of the interaction between parts of the rotor assembly according to the circle VI in figure 3; figure 7 shows a view in perspective of the rotor assembly of figures 4 and 5, with a maintenance part being removed from the rotor assembly; and figure 8 shows a disc of the reaction turbine according to figures 1-3.

DETAILED DESCRIPTION OF THE INVENTION

Figure 1 shows a hydrodynamic cavitation reaction turbine 1, simply referred to as the reaction turbine 1 hereafter, according to an exemplary embodiment of the invention. The reaction turbine 1 is a rotary mechanical device that is arranged for extracting energy from a liquid through hydrodynamic cavitation and for converting said cavitation energy into useful work. Hydrodynamic cavitation involves subjecting a liquid to rapid lowering of pressure that causes a phase change in parts of the liquid to vapor and the formation of vapor filled voids or cavities. The cavities collapse when subjected to a higher pressure, e.g. on impact with a surface, resulting in cavitation energy being released in the form of intense shockwaves.

As shown in figures 1 and 5, the reaction turbine 1 comprises a housing 2 with a cylindrical, circumferential inner wall 20 that defines a cylindrically shaped, internal volume V. The internal volume V is completely or almost completely filled with a suitable liquid L, e.g. water, liquid carbon dioxide (R744) or an emulsion of two or more liquids, e.g. water and biological oil. The reaction turbine 1 comprises a separation wall 21 that divides the internal volume V within the housing 2 into a storage compartment 22 for the liquid L and a reaction chamber 23 for creating the hydrodynamic cavitation.

As shown in figure 3, the reaction turbine 1 is provided with a rotation shaft 3 that is rotatably supported in a concentric position with respect to the cylindrical internal volume V and that defines a central rotational axis S of the reaction turbine 1. In this exemplary embodiment, the rotation shaft 3 extends through both the storage compartment 22 and the reaction chamber 23. As shown in figures 3 and 4, the reaction turbine 1 comprises a rotor assembly 7 that is mounted to the part of the rotation shaft 3 in the reaction chamber 23. The rotor assembly 7 will be described in more detail hereafter. As shown in figure 4, the rotation shaft 3 is formed as a hollow tube 30 that defines a hollow interior or duct 31, wherein the duct 31 is in fluid communication with both the storage compartment 22 and the reaction chamber 23 for transferring liquid L from the storage compartment 22 to the reaction chamber 23. In particular, at a free end 33, the rotation shaft 3 is arranged in open communication with the internal volume V at the storage compartment 22. Preferably, the rotation shaft 3 is formed as a hollow or tubular shaft protruding freely into the storage compartment 22, wherein the hollow shaft is open ended the free end 33. The rotation shaft 3 is further provided with discharge ports 32 circumferentially which are distributed around rotation shaft 3 in the reaction chamber 23 and which are in fluid communication with the rotor assembly 7 for directing liquid L from the duct 31 into the rotor assembly 7.

The liquid L is arranged to be hydrodynamically brought into cavitation within the rotor assembly 7, wherein the rotor assembly 7, as a result of the cavitation energy, is arranged to be rotated in a first rotational direction R1 around the central rotation axis S, while the liquid L in the reaction chamber 23 is flowing in an opposite, second rotational direction R2 in a manner which will be described hereafter in more detail.

As shown in figures 1 and 2, the reaction turbine 1 comprises a return conduit 4 that is arranged in fluid communication with internal volume V at both the storage compartment 22 and the reaction chamber 23 for receiving and transporting process liquid L from the reaction chamber 23 back to the storage compartment 22. In this exemplary embodiment, the return conduit 4 is arranged externally with respect to the housing 2. At a first end 41 the return conduit 4 merges with the reaction chamber 23, while at an opposite second end 42 the return conduit 3 debouches into the storage compartment 22. Both ends 41, 42 connect to the internal volume V in the first rotational direction R1. The first end 41 and the second 42 preferably merge with or debouch tangentially into the inner volume V with respect to the circumferential inner wall 20 of the housing 2 in the first rotational direction R1 for receiving and discharging the liquid, respectively, in the same direction as the direction of rotation of the remaining liquid L in the internal volume V. The liquid L debouching from the return conduit 4 into the storage compartment 22 at the second end 42 enters the internal volume V of the storage compartment 22 in the first rotational direction Rl, thereby contributing to the rotation of the liquid L in the storage compartment 22 in said first rotation direction Rl.

The return conduit 4 is preferably provided with a double walled circumferential wall 40 that is filled with a coolant for cooling the liquid L that is being transported through the return conduit 4. In this exemplary embodiment, the return conduit 4 is further provided with one or more vortex chambers 43, 44 for manipulating the liquid L to flow in a centripetal motion through the return conduit 4, thereby reducing the friction of the liquid L with respect to the return conduit 4 during transport.

As shown in figures 1, 2 and 5, the reaction turbine 1 further comprises a hydraulic accumulator 5 that is arranged in fluid communication with the internal volume V at the storage compartment 22 for maintaining the liquid L in the storage compartment 22 at a substantially constant, preset or adjustable pressure. In this exemplary embodiment, the hydraulic accumulator 5 is a compressed gas accumulator or a hydro-pneumatic accumulator. Alternatively, the pressure can be controlled by a mechanically actuated hydraulic accumulator (not shown).

As shown in figures 3 and 4, the reactor turbine 1 comprises a plurality of discs 6 which are concentrically mounted to and axially distributed along the rotation shaft 3 in the storage compartment 22. Each of the plurality of discs 6 has a flat or substantially flat surface 60 parallel to the flat surface 60 of the other discs 6 and extending perpendicular to the rotational axis S. The flat surfaces 60 of the discs 6 generate friction with the liquid L in the storage compartment 22, thereby inducing a laminar boundary layer flow or effect. In this manner, the liquid L can be given a smooth, non-turbulent rotation in the second rotational direction R2 prior to the liquid L entering the duct 31 of the rotation shaft 3 and ultimately the rotor assembly 7 in the reaction chamber 23. Alternatively, the discs 6 may be provided with suitably shaped blades or scoops (not shown) to further increase the friction with the liquid L. The rotation of the liquid L in the same first rotational direction R1 as the rotation shaft 3 results in a centripetal motion of the liquid L in the storage compartment 22. The centripetal motion reduces the pressure on the radial outside of the storage compartment 22, thereby considerably reducing the friction of the liquid L with the circumferential inner wall 20 of the housing 2 at the location of the storage compartment 22. As shown in figure 8, each disc 6 of the plurality of discs 6 is provided with a radially inner flow opening 61 for allowing the centripetally radially inwardly moving liquid L to flow towards the free end 33 of the rotation shaft 3.

As shown in figures 3 and 4, the rotor assembly 7 comprises a set of a first runner or rotor 71 and a second runner or rotor 72. The rotors 71, 72 are mirror-symmetrical with respect to a mirror plane perpendicular to the rotational axis S. Only the first rotor 71 will be described in more detail hereafter, while the one skilled in the art will understand that its functional features also apply to the second rotor 72. Also, it is worth mentioning that the reactor turbine 1 according to the invention also functions with a single rotor or three or more rotors (not shown).

As shown in figures 4, 5 and 7, the first rotor 71 comprises a disc shaped rotor body 73 formed by a first half 74 and a second half 75. The rotor body 73 is mounted concentrically to the rotation shaft 3 in a rotationally fixed manner so as to rotate together with the rotation shaft 3. The two halves 74, 75 mated together enclose a plurality of acceleration sections 76 which are evenly distributed around the rotation shaft 3 in the circumferential direction and which are arranged for accelerating the liquid L to obtain cavitation. The acceleration sections 76 will be elucidated further with reference to figure 5.

As shown in figure 5, the first rotor 71 according to this exemplary embodiment comprises three of the aforementioned acceleration sections 76, distributed, shifted or offset with respect to each other in the circumferential direction over angles of 120 degrees. The effect of the invention may however also be achieved by at least two acceleration sections or four or more acceleration sections (not shown). Each acceleration section 76 comprises a collection chamber 77 that is arranged in fluid communication with the duct 31 on the inside of the rotation shaft 3 via one of the discharge ports 32. The collection chamber 77 is arranged for collecting a certain mass or volume of the liquid L, prior to the liquid L entering the acceleration section 76, to increase the centrifugal forces and pressure exerted on the liquid L.

Radially outside and/or downstream of the collection chamber 77, the acceleration section 76 is provided with a non-linear, non-radial and/or curved acceleration channel 78 that is in fluid communication with the respective collection chamber 77 and that arcs, curves or spirals in the second rotational direction R2 such that the acceleration channel 78 promotes a centrifugal acceleration of the liquid L, opposite to the first rotational direction R1 of the first rotor 71. The liquid L in the collection chamber 77 is forced radially outwards by the centrifugal forces into the acceleration channel 78 and is accelerated considerably by centrifugal forces in the acceleration channel 78. In particular, the centrifugal velocities of the liquid L in the acceleration channel 78 reach a level in which the liquid L experiences a considerably pressure drop. The pressure drop causes at least part of the liquid L to change from a liquid phase to a gaseous phase, thereby forming a trail of gas filled bubbles or cavities in the liquid L. The expansion forces associated with the phase-change will, in particular in the case of the liquid L being liquid carbon dioxide (R744), considerably contribute to the rotation of the first rotor 71 in the first rotational direction R1.

The transfer of liquid L from the collection chamber 77 into the acceleration channel 7 8 and the subsequent pressure drop of the liquid L in the acceleration channel 78 draws new liquid L from the storage compartment 22 into the collection chamber 77 through the duct 31 in the rotation shaft 3. The drawing of liquid L from the storage compartment 22 further promotes the centripetal motion of the liquid L in the storage compartment 22.

Radially outside and/or downstream of the acceleration channel 78, at or near the radial outside of the first rotor 71, the acceleration section 76 is provided with an implosion chamber 7 9 that is in fluid communication with the acceleration channel 78. The implosion chamber 79 is arranged for receiving the accelerated liquid L with the trail of gas filled cavities from the acceleration channel 78. The acceleration section 76 is provided with an impact surface 80 that is placed at a predetermined angle with respect to the acceleration channel 78 to deflect the received accelerated liquid L out of the implosion chamber 79 substantially in a thrust direction T. In this example, the impact surface 80 is a flat surface that is placed at an angle in the range of 30 to 50 degrees with respect to the tangent of the downstream end of the acceleration channel 78. When the accelerated liquid L impacts the impact surface 80, the gas filled cavities violently implode, thereby releasing a large amount of energy in the form of acoustic shockwaves, micro-jet force and/or heat in the thrust direction T. The impact on the impact surface 80 results in a reaction force on and promoting the rotation of the first rotor 71 in the opposite first rotation direction R1.

The acceleration section 76 debouches into the inner volume V of the reaction chamber 23 at the radial outside of the first rotor 71 via a thrust nozzle 81 that extends in line with and is in fluid communication with the implosion chamber 7 9 in the thrust direction T. In this example, the liquid L that thrusts out of the thrust nozzle 81 is directed towards the first reaction element 85 in the second rotational direction R2, resulting in a reaction force on and promoting the rotation of the first rotor 71 in the opposite first rotation direction R1.

Each acceleration section 76 within the first rotor 71 generates cavitation in the liquid L in its respective acceleration channel 78, which liquid L subsequently impacts on the respective impact surface 80 to generate thrust and reaction forces that combined contribute to the rotation of the first rotor 71 in the first rotational direction R. The liquid L that enters the inner volume V of the reaction chamber 23 rotates in the opposite, second rotational direction R2.

As shown in figures 3 and 4, the first rotor 71 and the second rotor 72 are spaced apart in the direction of the rotational axis S to form a centripetal section 90 in between. The thrust nozzles 81 of the respective rotors 71, 72 debouch at a side of the rotor 71, 72 that faces the centripetal section 90. Directly opposite to the respective thrust nozzles 81 of the first rotor 71 and the second rotor 72 in the axial direction, the reaction turbine 1 is provided with a first reaction element 85 and a second reaction element 86, respectively. The reaction elements 85, 86 are fixedly attached to the housing 20 at the reaction chamber 23, axially directly adjacent to the rotors 71, 72 in the centripetal section 90. As best seen in figure 4, the reaction elements 85, 86 according to this exemplary embodiment are shaped as annular or ring-like bodies having a plurality of circumferentially distributed reaction holes 87. As shown in detail in figure 6 the reaction holes 87 are designed to interact with the liquid L that thrust out of the thrust nozzles 81 in the thrust direction T.

Specifically, the reaction holes 87 are designed to obstruct the flow of the liquid L in the thrust direction T and to maximize or to generate an optimal reaction surface for the liquid L, resulting in an oppositely oriented reaction force on the respective rotors 71, 72. Thus, the kinetic energy stored in the liquid L is effectively converted into rotational energy of the rotors 71, 72.

In this specific example, the first reaction element 85 comprises a plurality of layers, each having its own series of holes which together form the reaction holes 87. The holes per layer are slightly offset, e.g. over just one or two degrees, in the circumferential direction with respect to the holes of the other layer, thereby forming a stepped inner surface of reaction holes 87. Alternatively, the reaction elements 85, 86 may have a body with a plurality of suitably blades or scoops.

As best seen in figure 4, the centripetal section 90 is further provided with a first conically shaped element or cone 91 and a second conically shaped element or cone 92. The cones 91, 92 are fixedly mounted with their radially outer regions to the housing 2 at the reaction chamber 23 and extend radially inwards towards and concentrically with respect to the rotation shaft 3 between the respective rotors 71, 72. The cones 91, 92 are each provided with a conical surface 93 that tapers towards the rotor 71, 72 directly opposite to the respective cones 91, 92.

When the liquid L enters the inner volume V of the reaction chamber 23 at the centripetal section 90, the liquid L will initially be rotating in the second rotational direction R2, opposite to the first rotational direction of the rotors 71, 72 and the rotation shaft 3. The cones 91, 92 are arranged to force the liquid L to move in a laminar flow towards the rotation shaft 3 and as such promotes a centripetal movement of the liquid L as a result of centripetal forces towards the radial inside of the cones 91, 92. At the radial inside, at or near the rotation shaft 3, the cones 91, 92 are each provided with an escape port 94 with a diameter greater than the diameter of the rotation shaft 3 that allows the centripetally inwardly moving liquid L to escape to an evacuation section 95 that is located axially between the cones 91, 92. In the evacuation section 95, the liquid L is allowed to enter the first end 42 of the return conduit 4 in the second rotational direction R2, as shown in figures 1 and 2, to be returned via the second end 43 to the storage compartment 22 for reuse in the aforementioned process.

As shown in figure 7, the first half 74 and the second half 75 of the first rotor 71 can be taken apart to expose the respective cavitation sections 76. The area of the first rotor 71 that contains the implosion chamber 80 and the thrust nozzle 81 is formed as a separate, replaceable maintenance part 82 of the first rotor 71. The maintenance part 82, in particular the impact surface 81 thereof, is very susceptible to wear. Cavitation has been known to wear out or create metal fatigue in even the strongest metals. Therefore, the maintenance part 82 can be replaced altogether or can be taken out temporarily to replace solely the impact surface 81. For the latter replacement, the maintenance part 82 is provided with an access opening 83 that is normally sealed, that provides access to the impact surface 81. The impact surface 81 may be formed as an interchangeable insert. This provides the further advantage that the insert may be replaced by inserts with different shapes or angles, depending on the desired deflection and/or the liquid L that is being used.

The method of operating the reactor turbine 1 according to the invention will be described hereafter with reference to figures 1-8.

At start-up of the reactor turbine 1, an external torque is applied to the rotation shaft 3 in the first rotational direction R1 to start the rotation of the rotor assembly 7 in said first rotational direction R1. The torque is increased until the liquid L starts to cavitate in the acceleration channels 78 of the rotors 71, 72, as described above in relation to figure 5. As soon as cavitation occurs, the rotation of the rotor assembly 7 in the first rotational direction R1 will be promoted further by the forces and reaction forces resulting from the cavitation and the reactor turbine 1 will start to produce torque on the rotation shaft 3, which torque can be used to do mechanical work, e.g. driving a generator. The torque can be mechanically transferred via one end of the rotation shaft 3 that protrudes from the housing 2. In the event of the reactor turbine 1 operating under high pressure, e.g. with liquid carbon dioxide (R744), the energy can also be converted via a magnetic coupling.

In particular one or more of the forces and effects of the following group individually and/or in combination contribute in a more or lesser extent to a reduction of the amount of energy that is required to sustain the operation of the reactor turbine 1: the centrifugal forces of the liquid L being accelerated in the acceleration channels 78; the rapid expansion of said liquid L in the acceleration channels 78 as a result of the phase change to gaseous form; the implosion forces of the liquid L as the cavities implode on the impact surface 80 and the resulting phase change back to liquid form; the reaction forces exerted on the impact surface 80, the thrust forces of the liquid L in the thrust direction T; the reaction forces of said liquid L hitting the inner circumferential wall 20 of the housing 2 opposite to the thrust ports 79; the centripetal forces in the centripetal section 90; the centripetal forces in the storage compartment 95; and/or the reduced friction as a result of the aforementioned centripetal forces.

The cycle of the liquid L will now be briefly discussed.

As shown in figure 5 and as discussed above, the rotation of the rotor assembly 7 causes the liquid L in both rotors 71, 72 to be accelerated as a result of centrifugal forces. The liquid L impacts the impact surface 80 and thrusts out of the rotors 71, 72 in the thrust direction T to promote the rotation of rotors 71, 72 in the first rotational direction R1. As shown in figure 6, the liquid L impacts on the reaction holes 87 of the respective reaction rings 85, 86 directly after exiting the thrust nozzles 81, thereby causing a reaction force opposite to the thrust direction T. The reaction force acts on the rotors 71, 72 to further promote the rotation of said rotors 71, 72 in the first rotational direction R1. As shown in figure 3, the liquid L subsequently flows through the reaction holes 87 into the centripetal section 90 and is forced by the cones 91, 92 into a centripetal motion. Under influence of the centripetal forces, the liquid L spirals radially inwards and flows via the escape port 94 into the evacuation section 95, from where the liquid L is ultimately allowed to return to the storage compartment 22 via the return conduit 4 (see figures 1 and 2) . The pressure drop as a result of the acceleration of the liquid L in the acceleration channels 78 draws more liquid L from the storage compartment 22 via the duct 31 in the rotation shaft 3 back into the rotor assembly 7 in the reaction chamber 23, as shown in figure 3.

The reaction turbine 1 can be controlled to operate at process conditions that suit the liquid L that is being used. For a mixture of water and oil, the process pressure in the storage compartment 22 may be set with the use of the hydraulic accumulator 5 to a pressure of approximately 1 Bar and the coolant in the double walled return conduit 4 is controlled so that the temperature of the liquid L is within a range of 80 degrees to 90 degrees Celsius. For liquid carbon dioxide (R744), the pressure in the storage compartment 22 is increased to approximately 70 Bar at a temperature of approximately 30 degrees Celsius.

The aforementioned reaction turbine 1 can be designed to be very compact, e.g. with an outer diameter of less than 750 millimeters. The diameter of the rotors 71, 72 in this exemplary embodiment are in the range of only 400 millimeters to 600 millimeters, in particular approximately 450 millimeters. This allows for various small scale applications of the reaction turbine 1, e.g. in domestic use, e.g. for powering household appliances or as a compact boiler. The heat of the reaction turbine 1 can furthermore be used to heat and/or clean an external liquid flow, e.g. to remove pathogenic contaminations.

It is to be understood that the above description is included to illustrate the operation of the preferred embodiments and is not meant to limit the scope of the invention. From the above discussion, many variations will be apparent to one skilled in the art that would yet be encompassed by the scope of the present invention.

In summary, the invention relates to a reaction turbine comprising a reaction chamber with a rotor assembly that is supported on the rotation shaft, wherein the rotor assembly comprises a first rotor with acceleration sections for receiving liquid and for centrifugally accelerating the liquid to form vapor cavities in the liquid, wherein each acceleration section comprises a curved acceleration channel, an implosion chamber and a thrust nozzle, wherein the implosion chamber is provided with an impact surface that in use deflects the accelerated liquid towards the thrust nozzle while the cavities in the liquid implode and causes shockwaves in the liquid, wherein the thrust nozzle is arranged for directing the shockwaves of liquid out of the first rotor in a thrust direction intersecting with a first reaction element, causing an opposite reaction force that is exerted on the first rotor and thereby promoting rotation of the first rotor.

Claims

A reaction turbine comprising a housing with a cylindrical inner peripheral wall defining a reaction chamber with an inner volume which in use contains a liquid circulated through the reaction turbine, the reaction turbine having a rotation axis extending through the reaction chamber concentrically with respect to the inner peripheral wall and defining a axis of rotation of the reaction turbine, the reaction turbine further comprising a rotor assembly supported on the axis of rotation in the reaction chamber to be rotatable about the axis of rotation in a first direction of rotation, the rotor assembly comprising a first rotor with a plurality of acceleration portions for receiving fluid at or near the axis of rotation and for centrifugally accelerating the fluid in the direction of the radial outer side of the first rotor relative to the axis of rotation to form gas cavities in the fluid, each acceleration portion having a curved acceleration channel that supports centrifugal acceleration, an imploding chamber in fluid communication with and located downstream of the acceleration channel at or near the radial outer side of the first rotor relative to the axis of rotation, and a weir nozzle in fluid communication with and downstream lies of the imploding chamber, wherein the imploding chamber is provided with an impact surface which, in use, deflects the accelerated liquid from the acceleration channel towards the propulsion nozzle while the cavities in the liquid implode and cause shock waves in the liquid, the propulsion nozzle being adapted to directing the shock waves of the liquid from the first rotor in a direction of propulsion, the reaction turbine comprising a first reaction element which is arranged directly adjacent to the first rotor in the axial direction of the axis of rotation, the direction of propulsion being oriented in the direction of or in a second direction of rotation opposite to the first direction of rotation and wherein the direction of propulsion intersects with the first reaction element, the liquid in use impacting on the first reaction element and causing an opposite reaction force exerted on the first rotor and thereby supporting the rotation of the first rotor in the first direction of rotation.

The reaction turbine of claim 1, wherein the acceleration portions are evenly distributed in the circumferential direction of the first rotor relative to the axis of rotation.

The reaction turbine according to claim 1 or 2, wherein each acceleration portion comprises a collection chamber at or near the axis of rotation, which is in fluid communication with and upstream of the acceleration channel, the collection chamber being adapted to collect a volume of fluid prior to the entry of the fluid into the acceleration channel.

A reaction turbine according to any one of the preceding claims, wherein the reaction chamber comprises a centripetal portion that is directly adjacent to the first reaction element on its side facing away from the first rotor, the centripetal portion being adapted to receive the fluid from the weir nozzles of the respective acceleration sections and for forcing the fluid in a centripetal movement in the direction of the axis of rotation.

The reaction turbine of claim 4, wherein the centripetal portion comprises a first cone with a conical surface that tapers toward the first rotor and forces the liquid from the first rotor into a laminar centripetal flow toward the axis of rotation.

The reaction turbine of claim 5, wherein the reaction chamber further comprises an evacuation portion on the opposite side of the first cone relative to the first rotor, the first cone having an outlet port at or near the axis of rotation allowing the centripetal inward moving fluid flows from the centripetal portion to the evacuation portion.

Reaction turbine according to any one of the preceding claims, wherein the reaction turbine comprises a return line for returning the liquid that is received from the propulsion nozzles of the respective acceleration sections to the first rotor.

The reaction turbine of claims 6 and 7, wherein the return line is provided with a first end in fluid communication with the evacuation portion for receiving the fluid from the evacuation portion.

The reaction turbine according to claim 8, wherein the reaction turbine comprises a partition wall that divides the inner volume of the reaction turbine into the reaction chamber and a storage compartment, wherein the return line is provided with a second end in fluid communication with the storage compartment for recycling the liquid from the reaction chamber to the storage compartment, the storage compartment being in fluid communication with the first rotor for supplying the recycled liquid to the first rotor.

The reaction turbine of claim 9, wherein the axis of rotation extends through both the reaction chamber and the storage compartment, the axis of rotation being provided with a channel in fluid communication with the storage compartment and the first rotor for fluidly connecting the storage compartment with the first rotor.

The reaction turbine of claim 10, wherein the first rotor is rotatably mounted on the axis of rotation to be rotatable together with the axis of rotation in the first direction of rotation, the axis of rotation being provided with a plurality of discharge ports connecting the channel in fluid communication with the respective acceleration portions in the first rotor.

A reaction turbine according to claim 10 or 11, wherein the reaction turbine is provided with a plurality of disks which are rotationally fixed to the rotation axis in the storage compartment so as to be rotatable together with the rotation axis in the first rotation direction, the plurality of discs being adapted for supporting a boundary lowering fat in the fluid in the storage compartment relative to the axis of rotation.

The reaction turbine of claim 12, wherein the plurality of disks in use force the fluid to flow in a centripetal inward movement relative to the axis of rotation, each of the plurality of disks having a radially inner flow opening for allowing the centripetal fluid moving inward flows along the axis of rotation toward the location where the storage compartment is in fluid communication with the reaction chamber.

The reaction turbine of any one of claims 9-13, wherein the reactor turbine further comprises a hydraulic accumulator arranged in fluid communication with the storage compartment for controlling the pressure of the liquid within the inner volume of the reactor turbine.

The reaction turbine of any one of claims 7-14, wherein the return line is provided with at least one vortex chamber for manipulating the fluid to flow in a centripetal movement through the return line.

The reaction turbine of claim 15, wherein the return line is double-walled, the double wall in use being filled with a cooling medium to control the temperature of the liquid flowing through the return line.

A reaction turbine according to any one of the preceding claims, wherein the first reaction element is provided with a plurality of reaction holes for supporting the reaction force of the liquid relative to the first rotor.

A reaction turbine according to any one of the preceding claims, wherein the first rotor comprises a replaceable maintenance part, wherein at least the impact surface and preferably also the imploding chamber are located within the maintenance part.

A reaction turbine according to any one of the preceding claims, wherein the reaction turbine comprises a second rotor and a second reaction element which are functionally similar, equivalent or identical to the first rotor and the first reaction element, respectively, wherein the second rotor and the second reaction element are spaced apart from the first rotor and the first reaction element in the axial direction of the axis of rotation.

The reaction turbine according to claims 4 and 19, wherein the second rotor and the second reaction element are mirror symmetrical to the first rotor and the first reaction element in a plane perpendicular to the axis of rotation, the centripetal portion being located between the first reaction element and the second reaction element in the axial direction of the axis of rotation.

The reaction turbine according to claims 5 and 20, wherein the centripetal portion comprises a second cone with a conical surface that tapers in the direction of the second rotor for forcing the liquid from the second rotor into a laminar centripetal flow in the direction of the axis of rotation.

The reaction turbine of claims 6 and 21, wherein the evacuation portion is located between the first cone and the second cone in the axial direction of the axis of rotation.

A reaction turbine according to any one of the preceding claims, wherein the inner volume of the reaction turbine comprises the aforementioned liquid, preferably from the group comprising water, liquid carbon dioxide (R744) or an emulsion of two or more liquids, preferably an emulsion of water and oil.