Turbine with rotating blades

Abstract

The subject of the invention is a turbine with a stator (2), a rotor (1) rotating around the axis of the turbine Z, and a rotating blade comprising n rotating blades (3) equally spaced around the circumference of the rotor (1). The turbine comprises a pressurized chamber (4) surrounded by a slot (6) and a sealing chamber (7), between which an inlet channel (8) for the medium supply leads into the pressurized chamber (4). The slot (6), the sealing chamber (7) and the blades (3) are adapted to permanently seal both the slot (6) and the sealing chamber (7) with at least one blade (3). The rotation of the blades (3) may be ensured by a toothed gear, the angular velocity of the blades (3) being an integer multiple of the angular velocity of the rotor (1). The blades (3) may have a front wall (9) and a rear wall (10) of approximately conical or cylindrical shape.

Description

[Technical field]

[0001] The present invention relates to a turbine with blades capable of rotating about its axis, more particularly to a turbine having a pressurized chamber into which a medium is pumped and sealed by passing it through the blades. [Background technology]

[0002] In general, a turbine refers to a machine that converts the kinetic, thermal and pressure energy of a flowing medium into mechanical work. The energy conversion takes place in a blade grid consisting of blades on one or more rotors housed for rotation. The passage of fluid between the blades exerts a force on the blades, which causes the rotor to rotate. The blades may be of different shapes and sizes, may be rigidly fixed or rotate about their axis, and may have different angles between the blades and the axis of the turbine. The work done by the turbine can be used to produce electrical energy in combination with a generator connected to the rotor by a shaft.

[0003] Turbines have many applications. They are used, for example, as drive units in aircraft engines (for jet aircraft or as turboshaft units in helicopters and propeller aircraft). They are used to drive turbopumps, for example in rockets or gas pipelines. Their use is very important in the energy industry, where they are mainly used as the main drive machines for motor-generators, producing electrical energy for the public power grid. The turbines of some special types of pumped-storage hydroelectric plants are designed so that they can also function as water pumps (reverse).

[0004] Turbines are classified according to several aspects: according to the principle of energy conversion, they are classified as impulse energy, where the turbine changes the direction of a high velocity fluid flow, thereby having high kinetic energy, and reaction energy, where the turbine generates torque based on the reaction force as it changes the direction and speed of the fluid flow in the space between the rotor blades.

[0005] Turbines are further classified according to the medium they process. These can be water turbines, the best known of which are the Francis, Pelton, Kaplan or Van Michel turbines. Furthermore, gas turbines are well known and are classified into steam turbines and combustion turbines with heat engines. Another group are turbines that use the air flow to drive the rotor, i.e. wind turbines.

[0006] Depending on the design, turbines are divided into open types, in which the rotor is not closed by the stator body, and closed types, in which the rotor is closed by the stator body.

[0007] According to the direction of the medium flow, turbines are classified as axial flow turbines (axial turbines in which the fluid flow is mainly in the direction of the rotor's axis of rotation), radial turbines (radial turbines in which the fluid flow changes direction and most of the path is perpendicular to the rotor's axis of rotation), radial-axial turbines (radial turbines in which the fluid flow in the impeller changes direction from radial to axial) and tangential flow turbines (tangential flow turbines in which the fluid acts tangentially on the impeller).

[0008] In the current state of the art, turbines with partially rotating blades are well known, for example in the automotive industry, which are part of most vehicles with turbocharged engines and form an integral part of the turbocharger or supercharger. Turbines with rotating blades are also well known in the prior art. These variable area turbines (VATs) are adaptive components that, in combination with other adaptive engine elements such as adaptive fans, variable blade compressors, variable nozzles, etc., can provide significant advantages in the overall performance of gas turbine engines. These advantages can include, but are not limited to, reduced specific fuel consumption (SFC), reduced air temperature at the high pressure compressor outlet, improved throttle response, and extended part life.

[0009] A turbine with rotating blades is also described in patent number EP 3071796, which describes a two-flow gas turbine engine with a fan section, a compressor section, a combustion section and a turbine section. In this case, the blades rotate about their axis in a flow path defined between an outer diameter and an inner diameter. The blades rotate about their axis at a certain distance from the surface of the flow path. A drawback of this solution is high losses during the turbine operation, which can have a negative effect on the operating efficiency of the turbine. Another drawback is that considerable vibrations are generated during the turbine operation.

[0010] Another turbine with rotating blades is described in the patent document DE2602597A1. However, this solution has a significant medium leakage in the direction opposite to the drift of the blades, which reduces the efficiency. Moreover, this solution also generates significant vibrations, which affect, among other things, the lifespan of the turbine, etc.

[0011] Another example of a known turbine with rotating blades is the turbine described in patent document DE 883 563 C. However, the blades of this turbine have a concave and convex shape, which is necessary for this turbine in order to seal the slots, but which increases the area of ​​the slots and reduces the efficiency of the turbine.

[0012] It is therefore desirable to come up with a solution that increases the efficiency of the turbine and minimizes the rocking motion of the assembly. Summary of the Invention

[0013] The drawbacks of the solutions known from the state of the art are to some extent eliminated by a turbine with rotating blades, comprising a rotor adapted to rotate around the axis of the rotor Z and a stator, the rotor comprising blades arranged circumferentially, each blade rotating around its own axis. N blades equally spaced around the axis of the rotor, or the axis of the turbine Z, protrude from the outer surface of the rotor. Each blade comprises a front wall and a rear wall, and has two lateral edges, both of which are curved, the centre of curvature being on the same side from the blade, as viewed along the axis of the blade. The thickness of the blade is defined between the front wall and the rear wall. The lateral edges, and possibly other edges, of the blade may be sharp, rounded or take the form of a relatively narrow wall. In essence, the front wall and the rear wall are curved in the same direction, meaning that the blade has a concave-convex or concave shape, as viewed approximately in the axial direction of the blade. These walls preferably have a substantially cylindrical or conical area, for example not deviating from cylindrical or conical over the majority of their area by more than 1 millimeter, preferably by more than 0.5 millimeter, It does not necessarily have to be a region of revolution, for example it may be a region with an elliptical or parabolic base.

[0014] The thickness of the blade need not be constant across its width or length. The distance is preferably measured at each position of the blade as the distance between the front and rear walls, for example measured perpendicular to at least one of these walls.

[0015] The turbine further comprises a pressure chamber bounded by a front face of the pressure chamber and a rear face of the pressure chamber from both axial directions of the turbine, an inner peripheral wall of the pressure chamber and an outer peripheral wall of the pressure chamber. The faces and the peripheral wall are partly defined by the rotor and partly defined by the stator. For example, the faces can be planar areas perpendicular to the axis of the turbine. For example, the peripheral wall can be cylindrical or spherical. The start of the pressure chamber, i.e. its front end relative to the flow direction or the passage of the blades, is defined by a partition wall of two parts, and a slot for the entry of the blades into the pressure chamber is defined between both parts of the partition wall. Both parts can also be made from a piece of material and can be connected to each other, for example, at one face or one peripheral wall of the pressure chamber. The blades are adapted with respect to their shape to faithfully imitate the shape of the slot when they pass through it. Faithfully imitating means imitating the shape with only a small gap. When the blades pass through the slot, they are in a position with one edge facing forward. That is, during the passage, the front wall of the blade faces one part of the partition wall and the rear wall faces the other part. The shape of the front and rear walls, and in particular their curvature, are selected to achieve this faithful imitation. The aforementioned gap may be as small as possible while maintaining the free passage of the blades, for example less than about a millimeter, preferably less than half a millimeter, more preferably less than a tenth of a millimeter. The direction of the blade passage, i.e. the rotation of the rotor, is defined relative to the state when the turbine is operating as a generator. In general, the system can also function as a pump when supplying energy, the rotor of which then rotates relative to the direction of the blade passage introduced above.

[0016] When viewed in the direction of axis Z, they intersect on axis Z at an angle

number

[0017] The pressurizing chamber is firstly provided in the flow direction of the blade with an inlet channel for the medium supply to the pressurizing chamber and a channel having at least α, but

number

[0018] At each position of the rotor's rotation, the slot is sealed by at least one blade and the sealing chamber is sealed by at least one other blade. As mentioned above, it may not be a perfect seal and there may always be a certain gap between the wall of the pressurized chamber and the blade so that the blade can move freely. Since the efficiency of the blade depends, among other things, on the ratio of the cross-sectional area of ​​the sealing chamber to the area of ​​the slot, the area of ​​the slot is preferably as small as possible and the area of ​​the sealing chamber where the blade engages is preferably as large as possible, taking into account design requirements such as, for example, blade strength. The turbine described above allows this ratio to be achieved at a higher level than turbines known in the current state of the art, which also allows a more efficient functioning. The curvature of both blade walls in the same direction makes it possible to achieve a relatively thin blade thickness while maintaining sufficient blade strength when the blades engage and are most susceptible to deformation. The permanent sealing of both the slot and the sealing chamber prevents the unwanted passage of the medium, which also increases the efficiency. The medium discharge may be implemented either behind the sealing chamber or at the rearmost of the sealing chambers if there are more sealing chambers. For example, an opening may be provided for the free discharge of the medium. That is, for example, after leaving the pressurized chamber, the medium leaves the turbine either directly or through an outlet pipe into free space.

[0019] A turbine with the axis of rotation of the blades parallel to the axis of the rotor Z may be simpler to design than a turbine with the axes of the blades rotating differently. The walls defining the space for the movement of the rotor and the blades may also be planar and cylindrical (i.e. in the shape of a part of a rotating cylindrical shell). However, a turbine with the axis of the blades simultaneous with the axis Z may be more preferable in terms of the centrifugal forces and the risk of deformation of the blades caused by them. For example, a part of the wall defining the space for the movement of the rotor and the blades may be spherical. This simultaneous rotation may thus help to prevent undesired contact of the blades with the partition wall or the wall of the chamber due to deformation of the blades. The rotation of the blades is preferably dependent on the rotation of the rotor, in particular at least in the interval between the position at the entrance of the slot and the position at the exit from the sealing chamber, and more preferably in all rotation positions. This dependence is preferably ensured by a mechanical linkage of the two rotational movements, i.e. by the transmission of moments from the rotation of the rotor to the blades.

[0020] The turbine may be designed for gaseous media, the inlet channels then preferably being equipped with valves. The valves are, for example, electronically controlled or mechanically coupled to the rotor and adapted to open the inlet channel of each blade when a given blade enters the sealing chamber and close the inlet channel by a maximum of 0,6α during the rotation of the rotor. Preferably, only a maximum of 0,4α in the flow direction of the blade relative to the position of the rotor where the inlet channel is opened. α is the angular distance between the blades as defined above.

[0021] The use of such a valve increases the efficiency of the gas turbine, since not only the momentum of the supplied medium but also the expansion of the medium in the pressurized chamber after the valve is closed contributes to the rotation of the rotor blades, thus increasing the efficiency of the gas turbine. The moment or position of the rotor rotation at which the valve opens is preferably as close as possible to the moment when the sealing of the sealing chamber by a given blade begins. As close as possible here means, for example, within ±0,1α from this moment, preferably within ±0,05α. Even more preferably, the valve is opened only after sealing, for example at the latest at the moment when the rotor has turned one tenth of alpha. The valve must then be closed again, in order to seal the sealing chamber sufficiently in advance with another blade so that the expansion of the medium exerts a force on the given blade that opened and closed the valve. This advance is ensured by closing the valve after rotating it a maximum number of the aforementioned 0,6α. If the opening of the valve occurs after the sealing of the sealing chamber by the blade in question, the valve is preferably at a maximum value after opening 0,5α, more preferably at a maximum value of 0,25α after the valve is opened. At the same time, it is preferred not to close the valve until after the rotor has rotated only from its opening, 0.05α, for example, the valve may be closed after at least 0.1α, or at least 0.2α, etc.

[0022] The rotor may be provided with a speed sensor, for example an optical or magnetic sensor. The valve may then be an electromagnetic valve with a control unit which, based on the data from the speed sensor, opens and closes the valve in proportion to the rotational speed of the rotor. The valve may also be opened and closed mechanically. For example, the rotor shaft may be provided with a cam surface in the circumferential direction, which includes n equal parts around the circumference. The cam surface may be in contact with a connecting rod which is in contact with the valve, and based on the movement of the cam surface or each of its n parts, the valve opens at the appropriate moment as described above, after sealing the sealing chamber with the blades. The valve is then closed.

[0023] This turbine can operate with any angle between the axis of the blades and the axis of the rotor Z. The axes of the blades may all intersect on the Z axis or may be parallel to the axis Z. The value of this angle can then affect several other turbine design parameters, such as the angle between the side edges of the blades. The axes of the blades may have the same inclination, i.e. they may be parallel to the axis Z, or they may be close to each other in such a way that they intersect on the axis Z. For example, if the axes of the blades were assumed to be extended, they would be in approximately the same position as the axes of all the blades. Furthermore, this angle can affect the location of the center of the sealed chamber, or which walls and faces of the pressurized chamber are part of the rotor and which are part of the stator.

[0024] The number of blades n can be 5 to 100. Preferably, the number of blades n is 8 to 50, more preferably 8 to 30. The number of blades affects the beta and alpha angles introduced above, which are essentially the width of the blades and the length of the sealing chamber. The width of the blade also affects the width of the sealing chamber that must be sealable by the blade. Furthermore, as the number of blades increases, the magnitude of the deflection of the front and rear walls of the blade may decrease, which may affect their strength.

[0025] A turbine with rotating blades may comprise m pressurized chambers, each comprising a sealing chamber, a partition wall, a slot and an inlet channel, m being an integer between 1 and 10. Generally, m may be greater than 10. Essentially, each blade may leave a pressurized chamber through its sealing chamber and then enter the next pressurized chamber through its slot. For all m pressurized chambers with corresponding components, the features described above for these components apply, and other features described below may also apply to them. In particular, all pressurized chambers may thus have the same design. However, it is also possible to implement each pressurized chamber differently, such as sealing chambers of different lengths. Preferably, the blade is then adapted to rotate m revolutions relative to the rotor for each revolution of the rotor.

[0026] The turbine may be, for example, a water turbine, a steam turbine, or a gas turbine. The selection of the medium may affect some of the turbine design parameters, as determined by one of ordinary skill in the art.

[0027] Preferably, each blade has its own plane of symmetry in which the axis of the blade lies, and at the position of the blade in the center of the sealing chamber, the axis of the inlet channel forms an angle of less than 15° with the plane of symmetry of the blade. Essentially, a blade having its axis in the center of the sealing chamber will therefore have its area approximately perpendicular to the direction of the medium being fed, which is the most suitable angle for effective blade engagement and therefore for the rotation of the rotor. If the inlet channel is not straight and its axis is not a line, the given 15° angle is measured relative to the direction of the axis at the position where the inlet channel leads to the pressurized chamber, i.e. exactly relative to the direction of the flow of the medium entering the pressurized chamber.

[0028] Preferably, the blades are adapted to rotate with an angular velocity equal to an integer and non-zero multiple of the rotor angular velocity. For example, if the axis of the blades is approximately parallel to the axis of the turbine, the blades rotate in the same direction as the rotor, but they can also rotate in the opposite direction. In particular, the uniformity between the rotation of the rotor and the blades can be ensured by a toothed gear, which can also include, for example, a chain gear, a toothed belt, etc., transmitting a part of the rotor torque to the blades. Most preferred is a gear made of cogwheels. The said multiples are integers to maintain the same rotation of the blades at each entrance to both the slot and the pressure chamber. The advantage of this uniform rotation is to have the angular velocity of the blades rotating linearly dependent on the rotor angular velocity, resulting in a simpler design and minimizing vibrations and effects.

[0029] The blades may also be adapted to rotate in oscillating rotation, i.e., back and forth in a closed section of less than 360°. Such movement may primarily be achieved using a cam mechanism that guides the blade shaft and rotates it as the rotor rotates. Oscillating rotation may, for example, allow the use of more complex blade or sealing chamber shapes while maintaining the sealing of both the slot and the sealing chamber, reducing space requirements.

[0030] Preferably, each blade includes at its free end a reinforcing segment of increased thickness. The thickness is therefore a dimension determined by the width of the slot and the distance between the front and rear walls of the blade. The free end of the blade is the end located between the side edges and not associated with the rotational attachment of the blade to the rotor. This reinforcing segment provides the blade with a better stability when engaged, so that it is subject to less stress and deformation. As a result, a blade capable of withstanding a certain load value can be thinner with the reinforcing segment than a blade sized for the same load without the reinforcing segment in the remainder of its length. Thus, essentially, the cross section of both the blade and the slot is reduced, and therefore the ratio of the cross section of the sealing chamber to the slot is increased, which has a positive effect on the efficiency of the turbine. In a blade turbine with reinforcing segments, the slot also has an extension at the corresponding end, allowing the blade to pass freely through the slot and to seal it.

[0031] It is also possible to provide the reinforcing segments in the middle of the blade length or elsewhere, rather than at its free end. Moreover, each blade may also include multiple reinforcing segments spaced along the length of the blade. The shape of the slot reflects these extensions. Thus, for example, a blade may include three reinforcing segments of increasing thickness, the outer thickness of the reinforcing segments being constant or narrowing towards the free end of the blade. The slot then includes three extensions, allowing the blade to pass through these three extensions while at the same time sealing the slot with the blade. The extended segments may, for example, be elliptical.

[0032] Preferably, the thickness of each blade decreases towards its free end over the majority of the blade length. The majority of the length is preferably the majority of the length of the blade portion that exits the rotor, i.e. it does not include the blade portion that is retracted within the rotor. This ensures that the blade is stiffest at its rotational mounting position, where it is also most stressed, and at the free end, which possibly has the reinforcing segment. Further away from the mounting position, the thickness decreases, which again increases the efficiency of the turbine while still maintaining sufficient blade strength. A blade without reinforcing segments can be thin over its entire length.

[0033] The shape of the sealing chamber may be defined by the envelope of the compound motion of the blade edge through the sealing chamber for at least a portion of the length of the sealing chamber. This compound motion is thus a rotation around the axis of the blade and around the axis of the turbine. The desired shape of the sealing chamber for a particular blade shape can then be obtained, for example, by computer simulation. Depending on the blade shape, it may also be possible to obtain the desired shape of the sealing chamber analytically. The blade edge includes the side edge, and possibly also the free end at the location of the rotating attachment and / or the edge opposite the free end. The shape of the sealing chamber is also influenced by the number of blades, the location of the center of the sealing chamber, etc.

[0034] The shape of the slot, i.e. its cross section at its narrowest point, can be defined by the envelope of the compound movement of the front and rear walls of the blade passing through the slot. It is therefore defined by a portion of the envelope of the compound movement of the blade, which starts at the entrance of the blade to the slot and ends at the exit of the blade from the slot. As before, this is a rotating compound. For a given blade, the shape of the slot may again be obtained, for example by computer simulation. However, it is possible to make a design based on a specific slot shape, and from there obtain the shape of the blade based on the desired compound movement of the blade, i.e. to be located in the aforementioned envelope, forward and rearward. The rear wall seals the slot, the edges of the adjacent blades follow each other in the slot, and then the shape of the wall of the sealing chamber can be obtained from the shape of the blade and the given movement.

[0035] The axis of the blades may be parallel to the axis of the turbine, and the center of the sealing chamber is located away from the slot in the flow direction of the blades or in the opposite direction in the range of 65° to 85°. The axial direction of the blades is parallel, and the side edge of each blade is parallel to the axis of the blade. In that case, the shape of the front and rear walls of the blades may be approximately cylindrical. Furthermore, the axis of the blades may be perpendicular to the axis of the turbine, and the center of the sealing chamber is located away from the slot in the flow direction of the blades or in the opposite direction in the range of 80° to 100°. The side edges of each blade approach each other in the axial direction of the turbine. It is also possible to use this angle of rotation of the axis of the blades on the turbine. In that case, the side edges of the blades are further away from each other towards the axis. The blades are located in the space defined by the rotor and face each other with their free ends. In that case, the front and rear walls may be approximately conical. These two cases of inclination of the axis of the blades essentially represent limiting cases, and in general, the inclination of the axis with respect to the axis of the turbine may be anywhere between 0° and 90°. Alternatively, the rotation of the blades may be between -90° and 90°, since the rotation is possible in intervals of 180°. Thus, at an angle of -90°, the free ends of the blades may be oriented to a point on axis Z, with their axes lying in a plane. Also, at an angle of 90°, the free ends of the blades may be turned away from each other, with their axes lying in the same plane. It may be preferable to rotate the axes of the blades simultaneously about axis Z.

[0036] The blades may also be provided with a connecting ring, which extends in the entire circumference of the turbine and has a constant cross section. The free ends of the blades are rotatably attached to the ring, which may be slidably attached to the stator. The slots then fit their shape into the passage of the ring, which permanently seals them at that position. Similarly, the shape of the ring may also affect the cross section of the sealing chamber. Thanks to the connecting ring, the free ends of the blades support each other in such a way that their deflection is limited, in particular the deflection of the blades during engagement. As a result, it is possible to create thinner blades while maintaining sufficient strength, which may increase the efficiency of the turbine. The connecting ring can be used for any of the turbines mentioned above, in particular for any angle of rotation between the axis of the turbine and the axis of the blades, as well as for any number and shape of blades, any value of the parameter m, any used medium, etc. The cross section of the ring may be chosen so that it is sufficiently rigid, but at the same time can be easily bypassed by the medium, in particular when the ring passes through the mouth of the medium that feeds the pressurized chamber.

[0037] The turbine of the present invention may be used, for example, to generate electrical energy or in turn to pump a fluid. Use in flow meters, particularly turbine flow meters, is also possible. Flow meters using such turbines may be more tolerant to changes in flow rate and therefore may ensure, for example, more accurate measurements over a wider range of possible flow rates.

[0038] The summary of the invention will be further clarified using examples of its embodiments which are described with reference to the attached drawings. [Brief description of the drawings]

[0039] [Figure 1] 1 shows a schematic view of the blade and pressure chamber arrangement of a turbine with rotating blades according to the invention in an axis Z view, the axes of the blades are parallel to the axis Z and one of the blades is currently in a slot, at the same time the previous blade exits the slot, which is sealed by both blades. [Diagram 2] The different rotational views of the rotor in Fig. 1 are shown diagrammatically. There is one blade in the slot that seals the slot itself. [Diagram 3] FIG. 3 is a perspective view of a rotor with blades and a portion of the stator of the turbine of FIG. 1 and FIG. 2. The inner and outer peripheral walls of the stator with both parts of the partition wall and the outer wall of the sealing chamber are also shown. [Figure 4] 1 shows a schematic cross-sectional view of another embodiment of a turbine with the axes of the blades perpendicular to the axis of the turbine, the plane of the cross section is perpendicular to and intersects the slot, such that one of the blades is just entering the slot while the previous blade has just exited the slot and this slot is sealed by both blades. [Diagram 5] 5 shows a schematic diagram of the rotor of FIG. 4 at different rotations. There is one blade in the slot that seals the slot itself. [Figure 6] 1 shows a schematic cross-sectional view of the interior of a sealing chamber, the sealing chamber being sealed by two blades, the plane of the cross-section being approximately perpendicular to the axis of the blades within the sealing chamber; [Figure 7] 7A-7C are views of the rotor of FIG. 6 at different rotations, where the sealing chamber is sealed by a single blade at the illustrated position of the rotor rotation while the previous blade leaves the sealing chamber and the next blade takes its place. [Figure 8] FIG. 8 is a cross-sectional view of the gear mechanism for the first half of the turbine blade of figures 4 to 7. Both the turbine and slot axes lie in the plane of the section. [Figure 9] FIG. 8 is a cross-sectional view of the gear mechanism for the second half of the turbine blade of figures 4 to 7. The axis of the turbine and the centre of the sealing chamber lie in the plane of the cross-section. [Figure 10] FIG. 1 is a cross-sectional view of a turbine in which the axis of the blades is perpendicular to the axis of the rotor, with one of the blades located in the slot and the other located in the center of the sealed chamber. [Figure 11]1A-E show schematic diagrams of turbine blades with their axes perpendicular to the rotor axis and some exemplary blade cross sections, and also show detailed views of the free end of the blade with a reinforcing segment. [Figure 12] 1 shows a schematic representation of several exemplary cross-sections of turbines along their axis, the turbines in which differ from one another by a rotation of the axis of the blades relative to the axis of the turbine, expressed as a gamma angle; [Figure 13] 1 illustrates a schematic of an embodiment of a turbine of the present invention having a valve in an inlet channel coupled by a pair of arms with cam surfaces on a rotor; [Figure 14] 13A and 13B show schematic diagrams of the β angle of the blades at the entrance to the slots in an embodiment having their axes parallel to axis Z. [Figure 15] 13A and 13B show schematic diagrams of the β angle of the blades at the entrance to the slots in an embodiment having their axes parallel to axis Z. [Figure 16] 1 shows diagrammatically several detailed views of the slots and the beginning of the pressure chamber of a turbine with the axes of the blades perpendicular to the axis Z. The views are in a direction parallel to the slots and differ from one another due to the rotation of the rotor. [Figure 17] Schematically, several views of the slots and pressure chambers of a turbine with the axes of the blades perpendicular to the axis Z. The views are in a direction parallel to the axis Z and the views are in a direction parallel to the slots, which differ from each other due to the rotation of the rotor. [Figure 18] 1 shows diagrammatically several detailed views of the sealing chamber of a turbine with the axes of the blades perpendicular to the axis Z. The views are in a direction approximately parallel to the axes of the engaged blades and differ from one another with the rotation of the rotor. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0040] The invention will now be further explained by way of example embodiments with reference to the respective drawings, in which:

[0041] The object of the invention is a turbine with rotating blades 3. This turbine comprises a rotor 1 rotating about the axis of the turbine Z and a stator 2 at least partially surrounding the rotor 1. At least one annular cavity is defined between the rotor 1 and the stator 2, in which the blades 3 are arranged. The blades 3 are equally spaced on the outer circumference or wall of the rotor 1 and rotatably connected thereto. The rotation of the blades 3 relative to the rotor 1 defines for each blade 3 an axis of the blade 3. The axis of the blade 3 intersects at a point on the axis Z or is parallel to the axis Z (i.e. substantially intersects the axis Z at infinity). In the cavity with the blades 3 there is a pressurized chamber 4 to which an inlet channel 8 leads for supplying the working medium. The beginning of the pressurized chamber 4, i.e. the position where the blades 3 enter the pressurized chamber 4 when the rotor 1 is rotating, is defined by a partition wall 5. The partition wall 5 comprises two parts, between both parts a slot 6 is defined for the narrow passage of the blades 3, through which the pressurized chamber 4 begins. Both parts of the partition wall 5 may be rigidly connected to each other and may be of a single material, but are separated and distinguishable from each other by the slot 6. The end of the pressurized chamber 4 is defined by a sealing chamber 7, which is also adapted for the narrow passage of the blades 3, but unlike the slots 6 therein, the blades 3 pass with the greatest possible area exposed to the working medium fed into the pressurized chamber 4 through the inlet channel 8. Both the slots 6 and the sealing chamber 7, together with the shape and arrangement of the blades 3, are adapted so that the slots 6 and the sealing chamber 7 are permanently sealed, i.e. with each rotation of the rotor 1, and molded in the best possible way by at least one blade 3. The sealing may be defined with a small gap, for example of a millimeter in a few tens of minutes, preferably less than a millimeter in a few tens of minutes, to ensure the free passage of the blades 3 without substantial leakage of the medium between the blades 3 and the walls of the partition wall 5 or the sealing chamber 7. This gap may also be selected with respect to the thermal expansion of the blades 3, in order to avoid friction of the blades 3 against the area on the stator 2, for example if the medium is steam.

[0042] Basically, each blade 3 is therefore adjustable by the rotation of the rotor 1 to several positions, in particular at least the following positions: a position at the entrance to the slot 6, in which this blade 3 starts to seal the slot 6 and enters it with its outer edge 11 lying forward, a position at which this blade 3 stops sealing the slot 6 so that only its opposite side edge 11 is substantially in the slot 6 and the following blade 3 is in a position at the entrance to the slot 6, a position at which it exits the slot 6, in which the side edges 11 of the blade 3 are as close as possible to parts of the walls defining the sealing chamber 7 or abut them so that the blade 3 enters said chamber and essentially its front wall 9 or rear wall 10 is in front, The position of the beginning of the sealing of the sealing chamber 7 by the blade 3, and at the latest the moment the blade 3 reaches this position, a subsequent blade 3 comes to its position of the start of the sealing of the sealing chamber 7, and at least between these positions of the start and end of the sealing of the sealing chamber 7, the given blade 3 can be called the engaged blade 3, which is the position of the end of the sealing of the sealing chamber 7 by the blade 3, and exiting the sealing chamber 7 at the position of the end of the sealing can also occur with the front wall 9 or the rear wall 10 in front (i.e. the same wall in front as when entering the sealing chamber 7 and the sealing chamber 7 begins).

[0043] The shape of the blade 3 is determined so that, when passing through the slot 6, the blade 3 fits as tightly as possible against the area or edge of the partition wall 5 in which the slot 6 is defined. This shape is therefore defined by the shape of the slot 6 and the combined movement of the blade 3 with its rotation around the axis Z and around the axis of the blade 3. Essentially, the shape of the blade 3, in particular the shape of its front wall 9 and rear wall 10, and possibly also the shape of at least a part of its edges, is therefore defined by the envelope of the combined relative movement between the blade 3 and the slot 6 or the area and edges that define the slot 6. The slot 6 is made as narrow as possible while maintaining a sufficient strength of the blade 3 to ensure the highest possible efficiency of the turbine, in particular the highest possible ratio of the area of ​​the sealing chamber 7 to the area of ​​the slot 6. The strength of the blade 3 must be sufficient to prevent damage or deflection when the blade 3 is engaged in the sealing chamber 7. The stresses on the blade 3 are significantly smaller when passing through the slot 6 or when the blade 3 rotates by its width along the direction of rotation of the blade 3 around the rotor 1. Each blade 3 comprises a front wall 9 and a rear wall 10, connected by the edge of the blade 3 and defining the thickness of the blade 3. Both of these walls are curved, and preferably both of these walls take the form of a curve in a cross section through a plane perpendicular to the axis of the blade 3, the centre of curvature of which lies on the same side from the blade 3 over the majority of such cross section. For example, both the front wall 9 and the rear wall 10 may be at least partially defined by a cylindrical or conical wall, the front wall 9 having a different radius of curvature or a different axial position than the rear wall 10, ensuring the above requirement for the best sealing of the slot 6 during the combined movement of the blade 3.

[0044] Preferably, the blade 3 narrows towards its free end over at least a part of its length. The length is the dimension of the blade 3 measured along its axis. The free end is the end at which the blade 3 is not rotatably attached to the rotor 1. This narrowing allows a further reduction in the cross section of the slot 6, which has a positive effect on the efficiency. At the position of the rotary attachment, the blade 3 is most stressed by the pressure of the medium, so that there it needs to be thicker. Near the free end, the blade 3 may then be extended in its thickness direction by a reinforcing segment 12, whether or not it narrows in the longitudinal direction. Thus, in particular, the blade 3 may have an extended border along the free end in order to increase the strength of the blade 3. The shape of the slot 6, and preferably the shape of the sealing chamber 7, must also reflect this extension. As a result, the slot 6 also extends at the corresponding end, and preferably the sealing chamber 7 also extends at the corresponding position. Alternatively or additionally, the deflection of the blade may be limited in any embodiment by a connecting ring. This ring interconnects the free ends of all the blades 3 and has a constant cross section along its entire length, i.e. along the entire circumference of the turbine. The shape of the slots 6 is adapted to seal at the corresponding ends by means of a passing ring. Similarly, the shape of the sealing chambers 7 may be adapted, for example, their walls may have grooves in which the rings slideably seat. The free ends of the blades 3 are rotatably attached to the ring, for example, a pin or mandrel protruding from each free end that fits into a circular opening in the ring, or bearings may also be used.

[0045] The pressurized chamber 4 is defined by the outer surface of the rotor 1 and the inner surface of the stator 2. These surfaces define the inner and outer peripheral walls of the pressurized chamber 4 and further define the front surface 13 of the pressurized chamber 4 and the rear surface 13 of the pressurized chamber 4 in the turbine axial direction. For example, the surfaces can be planes. Whether the surfaces or the peripheral walls are formed by the rotor 1 or the stator 2 can be influenced by choosing the angle between the axis 28 of the blades 3 and the axis of the turbine. In the passing direction of the blades 3, the pressurized chamber 4 is further defined by the partition wall 5 with the slots 6 and the sealing chamber 7, as described above. When viewed in the direction of the axis Z, it is possible to define a coordinate system of the turbine, for example a right-hand polar coordinate system. Its origin is the projection of the axis Z and the zero axis, i.e. the axis along which angles are measured in the clockwise direction in this system is the axis passing through the slots 6 and in particular through their narrowest position. If the narrowest point of the slot 6 has a non-negligible length in the flow direction 29 of the blade 3, the zero axis and the point where the blade 3 enters the pressure chamber 4 can, for example, be located in the centre of this narrowest point.

[0046] Between the slot 6 and the beginning of the sealing chamber 7, the pressurized chamber 4 extends so that the supplied medium can pass around the blade 3. The sealing chamber 7 is then practically a constriction of the pressurized chamber 4, where the medium can no longer pass freely around the blade 3 and must therefore move the blade 3 to rotate the rotor 1. The shape of the sealing chamber 7 is therefore essentially the envelope of the movement made by the edge of the blade 3 passing through a given position, and this movement is therefore a composite of two rotations. The length of the sealing chamber 7, i.e. the size of the angular interval measured in the coordinate system introduced above, is then defined in relation to the number of blades 3n located on the rotor 1 in the cavity, taking into account such a way that the sealing chamber 7 is always sealed by at least one blade 3, i.e. the following blade 3 enters the sealing chamber 7 at the latest at the moment when the previous blade 3 leaves it. The minimum length of the sealing chamber 7 is therefore determined by the angular interval 3n, i.e. ...

number

[0047] The permanent sealing of the sealing chamber 7 is ensured in particular by its length relative to the number of blades 3, in other words by the fact that the distance between adjacent blades 3 is smaller than the length of the sealing chamber 7. The permanent sealing of the slot 6 is ensured in particular by the width of the blades 3, i.e. by the dimension measured approximately perpendicular to both the thickness and the length. This width is defined by the number of blades 3 and, in the state where a particular blade 3 enters the slot 6 with its side edge 11,

number

[0048] The number of blades 3n may range, for example, from 5 to 100, more preferably, for example, from 8 to 50, more preferably from 8 to 30. The turbine may include m cavities, each of which includes its own pressurized chamber 4. For example, m is an integer between 1 and 10. Each pressurized chamber 4 includes a slot 6, a sealed chamber 7, and a medium inlet channel 8. The axis of this channel may be approximately perpendicular to the cross section of the sealed chamber 7 through a plane passing through the axis of the turbine and the center of the sealed chamber 7, regardless of the value of the parameter m. It may be, for example, at an angle of 75 to 105°, more preferably 85 to 95°. In other words, the blade 3 may have a plane of symmetry that is approximately parallel to the axis of the medium inlet channel 8 when the axis of the blade is located in the center of the sealed chamber 7. The supplied medium thus comes into contact with the blade 3 in the sealed chamber 7 and engages it at an angle appropriate to achieve the highest possible efficiency. That is, the medium is supplied approximately perpendicular to the area of ​​the blade 3. The turbine may be, for example, a water, steam, or gas turbine. When supplying energy and rotating the rotor 1 in the opposite direction, the turbine can also function as a medium pumping device or pump. If m is greater than 1, it is preferred that the rotation of the blades 3 is continuous with respect to the rotation of the rotor 1 with a gear ratio of m:1, i.e. the blades 3 rotate relative to the rotor 1 with m rotations per revolution of the rotor 1 relative to the stator 2.

[0049] The rotational speed of the blades 3 may be directly proportional to the rotational speed of the rotor 1. This may be achieved, for example, by using a toothed gear. For example, the rotation of the blades 3 relative to the rotation of the rotor 1 may be in a 1:1 ratio. For example, a gear may be attached to the shaft of the blades 3 directly or via another gear, which engages with a rigidly mounted gear whose centre is on the axis of the turbine. The choice of gear may then be used to achieve the desired gear ratio, which may then affect or be influenced by the shape of the elements of the pressurized chamber 4, in particular the shape of the slot 6, the blades 3 and / or the sealing chamber 7. For example, a particular shape of the slot 6 may require the blades 3, i.e. their front wall 9 and rear wall 10, to be curved further around their axis if the rotation of the blades 3 is faster than that of the rotor 1.

[0050] The rotation speed of the blades 3 may also be variable, in particular the blades 3 may have an oscillating movement, i.e. rotate around their axis in a closed interval. For example, they may rotate back and forth in a range of less than 120°, or less than 180°, or less than θ=180°, at least less than 360°. This movement may in particular be achieved by a cam mechanism, which may be rigidly arranged on the stator 2 and may be in contact with an element attached to the shaft of the blades 3. For example, the cam mechanism may be implemented in such a way that the blades 3 do not rotate around their own axis when they are arranged in the sealing chamber 7, or at least when they are sealing the sealing chamber 7. After leaving the sealing chamber 7, the blades 3 may then rotate in the opposite direction to their initial position. If multiple pressurized chambers 4 are used, their respective blades 3 may likewise rotate around their own axis.

[0051] The choice of the oscillating movement again influences or is influenced by the shape of the elements of the pressurized chamber 4. In the case of a specific choice of the shape of the slot 6, the shape of the blade 3 is influenced by the combined movement of the blade 3 in the area of ​​the slot 6, whether the rotation is continuous or oscillatory, and by the shape of the slot 6. The sealing chamber 7 is then influenced by the shape of the blade 3 and their combined movement. The shapes of these components can be obtained, for example, by computer simulation, where the choice of the shape of the slot 6 and, if necessary, the choice of the rotatable movement of the blade 3 (which is defined, for example, by the gear ratio or the shape of the cam mechanism, etc., and can be selected, for example, with regard to the selected medium, the space possibilities, the noise requirements, the vibrations, the life, etc.) are used to calculate the shape of the blade 3 and of the walls of the sealing chamber 7. In some embodiments, the blade 3 may rotate continuously in the same direction, but at a variable speed. That is to say, it is neither an oscillating movement nor a movement with a fixed gear ratio. It is also possible to rotate the blade 3 in the opposite direction to the direction in which the rotor 1 rotates.

[0052] In the case of a turbine of the invention designed for a gaseous medium such as water steam, when the inlet channel 8 is equipped with a valve 24, the opening and closing of which preferably opens and closes the inlet channel 8 and starts and stops the medium supply to the pressurized chamber 4. The opening and closing of the valve 24 is synchronized with the rotation of the rotor 1 or with the passage of each blade 3 through the pressurized chamber 4.

[0053] For each blade 3, the valve 24 is preferably opened immediately after the sealing chamber 7 by the blade 3. Then the medium enters the pressurized chamber immediately after sealing and starts to push this blade 3. Then the valve 24 is closed when the rotor 1 has rotated by an angle δ (delta) relative to the rotation angle when the valve 24 is open for this blade 3. Preferably, the angle δ is at most 0.6 times α, i.e. equal to 60% of the rotation by the distance of the blade 3. Preferably, the angle δ is at most 0.3 times α. The minimum size of the delta angle is preferably 0.1 times alpha. After the valve 24 is closed, the medium in the pressurized chamber 4 is closed on one side by the slot 6 and on the other side by the sealing chamber 7 and from the direction of the inlet channel 8 by the valve 24. The medium expands and continues to push the blade 3, taking into account that it seals the sealing chamber 7. If the sealing chamber 7 is sealed by several blades 3, the medium will push the blade 3 further back, i.e. closer to the inlet channel 8.

[0054] Preferably, the valve 24 opens as close as possible to the moment of sealing of the sealing chamber 7 by the target blade 3. For example, the opening may be performed ±0.1α, more preferably ±0.05α, of the rotation angle of the rotor 1 corresponding to the sealing of the sealing chamber 7 of the target blade 3. That is to say, the opening of the valve 24 can take place just before the sealing of the sealing chamber 7, but preferably after and just after the sealing.

[0055] The opening and closing of the valve 24 can be ensured electronically, i.e. the valve 24 can be an electromagnetic valve controlled with respect to the speed of the rotor 1. Thus, the electromagnetic valve and a speed sensor of the rotor 1 can be provided with a control unit, which receives data from this sensor and opens and closes the valve 24 with respect to the rotation of the rotor 1 as described above. Furthermore, the opening and closing can be ensured mechanically by a mechanism directly coupled to the rotor shaft such that each rotation through the alpha angle ensures the opening and closing of the valve 24 with respect to the position of the blades 3 as described above.

[0056] An embodiment of a turbine with a valve 24 is shown in FIG. 13. In this embodiment, the axis of rotation of the blades 3 is parallel to the axis of the rotor 1, but such a valve 24 can be arranged in a turbine with any number and shape of blades 3, etc., with any rotation of the axis. The valve 24 may take the form of a lid shaped to seal the outlet from the inlet channel 8. In the illustrated embodiment, the movement of the valve 24 is ensured by a cam surface 25 of the valve 24 located around the axis of rotation on the rotor 1. This cam surface 25 for the valve 24 includes n teeth and n recesses between them and is in contact with a first arm 26, which is static with respect to the rotation of the rotor 1 and is slidably mounted on the stator 2 and is provided with a roller at each position to reduce friction. At the end remote from the cam surface 25 for the valve 24, this first arm 26 is supported by a second arm 27 rotatably mounted on the stator 2. This second arm 27 is supported by the valve 24 such that the rotation of the second arm 27 takes place within a closed interval defined by the size of the shift of the first arm 26, which in turn is defined by the teeth and the recess of the cam surface 25 for the valve 24, which thereby ensures that the valve 24 shifts between the closed and open positions. The contact between the valve 24 and the second arm 27 is also ensured by a roller to prevent wear of the valve 24 and the second arm 27.

[0057] When the first arm 26 is in contact with a recess in the cam surface 25 of the valve 24 (see FIG. 13), the valve 24 is closed. When the first arm 26 is in contact with a tooth of the cam surface, the valve 24 is open. The width of these teeth therefore influences the flow time of the medium into the pressurized chamber 4 of each blade 3. In the embodiment shown, the suspension of the second arm 27 by the upper part of the valve 24 is repelled to ensure the closure of the valve 24. This suspension can also help to damp shocks and vibrations. Alternatively, the cam mechanism for the movement of the valve 24 can be implemented with, for example, a single arm, or multiple arms, or the connecting rod may be supported by a cam that is directly part of the valve 24.

[0058] In FIG. 14, for the blade 3 at the entrance to the slot 6, the angle β is shown, which is defined by the axis of the blade 3 parallel to the axis Z. This angle is defined by the junction of the axis Z with the axis 28 of the blade and by the junction of the axis Z with the slot 6, when viewed in the direction of the axis Z. In this figure, i.e. projected onto a plane perpendicular to the axis Z, both axes are points. The narrowest place of the slot, which defines the beginning of the slot, in particular the pressurized chamber, in which the leading edge of the blade 3 is located, if this blade is located at the entrance to the slot 6, in this figure, its position is a line segment facing the axis Z in FIG. 14. This line segment is defined between the tips of the two parts of the partition wall 5. For the blade 3 at the exit from the slot 6, this angle β is similar, which means that the blade 3 always meets at these two positions in the slot 6 and is therefore permanently sealed.

[0059] FIG. 15 shows the situation of FIG. 14 in another embodiment, this time with the axis 28 of the blade perpendicular to the axis Z. In the projection of a plane perpendicular to the axis Z, the axis of the blade 3 in its position at the entrance to the slot 6 passes through the projection of the axis Z. The slot 6, or its narrowest point, is again a line segment in this figure, which joins with the dashed line in FIG. 15. In this view, one part of the partition wall 5 is hidden behind the blade 3, and the other part is not visible because the plane of the section passes between them, but the narrowest point of the slot can again be defined by the tips of these parts. Between them the slot 6 is defined. These parts can be seen better in FIGS. 4 and 5.

[0060] The above features, individually or in combination with each other, can be applied to the turbine of the invention at any angle between the axis 28 of the blade 3 and the axis of the turbine.

[0061] In a first exemplary embodiment shown in figures 1-3, the axis of the blade 3 is parallel to the axis of the turbine Z. For a slot 6 defined by the shape of a line segment, the blade 3 has a front wall 9 and a rear wall 10 that are approximately in the shape of a cylindrical section, the axis of the cylinder of the front wall 9 not coinciding with the axis of the cylinder of the rear wall 10 and / or the radii of these cylinders are different such that both the front wall 9 and the rear wall 10 seal the slot 6 when passing through it. The walls of the rotor 1 and the stator 2 that define the cavity with the blade 3 may be cylindrical such that the side edges 11 of the blade 3 may then be straight and parallel to each other. In a preferred embodiment with an extension of the free end of the blade 3, the slot 6 also includes an extension at the end, and both the edge and the wall of the blade 3 have a completely corresponding shape (rounded, bent, etc.) in the area of ​​the extension. However, the sealing function of the blade 3 is maintained throughout the entire passage through the slot 6 and along the entire length of the slot 6. The slot 6 (i.e. its narrowest point located between the opposing edges of the portions of the partition wall 5) is in this embodiment parallel to the axis Z. The number of blades 3n may be, for example, between 6 and 24. The width of the blades 3 is then selected in relation to the number of blades 3 such that adjacent blades 3 meet in the slot 6 or are permanently sealed by at least one blade 3.

[0062] As can be seen from figures 1 and 2, the partition wall 5 is attached in one part to the inner peripheral wall of the pressurized chamber 4 and in the other part to the outer peripheral wall of the pressurized chamber 4, both of these walls being static in this embodiment. In the attached position, the partition wall 5 is at its thickest to provide sufficient strength, and towards the slot 6 between the parts it narrows, narrowing in the direction of the passage of the blades 3 and the parts of the partition wall 5. The parts of the partition wall 5 do not impede the continuous movement of the blades 3. In this embodiment, the blades 3 rotate continuously, and for every revolution of the rotor 1 relative to the stator 2, the blades 3 make one revolution about their own axis relative to the rotor 1. However, it is also possible to combine this angle of rotation of the axis of the blades 3 with different gear ratios between the rotation of the blades 3 and the rotor 1, and also with an oscillating movement or a movement at a rotational speed of the blades 3, which is not directly proportional to the speed of the rotor 1.

[0063] In this embodiment, the pressurized chamber 4 has a length of 100° measured in the coordinate system introduced above. The sealing chamber 7 has its center in a direction of 75° from the slot 6 and has a length of about 30° inside it and about 50° outside it when viewed on the axis of the turbine. The beta angle introduced above is therefore 15° in this embodiment and the width of the blade 3 is about 30°. The position of the center of the sealing chamber 7 can vary, for example, by ±10°. Its length may also vary, but must be such that the sealing chamber 7 is permanently sealed by one of the blades 3. For example, the inlet channel 8 for the medium supply may be parallel to the zero axis as in the embodiment shown, but may generally be inclined, for example, by ±15°. Preferably, the supply medium faces directly at least approximately the area of ​​the blade 3 in the sealing chamber 7.

[0064] The shafts of the blades 3 may pass through the wall of the rotor 1, behind which the shafts may be provided, for example, pressed into a rigid gear if the size of the turbine and the selected gear ratio allow it, or in any other rotating gearing attached to the stator 2, which is pressed into a rigid gear. In the case of the oscillating movement of the blades 3, instead of a toothed gear, a cam mechanism may be used, shaped to ensure the desired movement of the blades 3 during their passage through the sealed chamber 7.

[0065] In the second exemplary embodiment shown in Fig. 4 to Fig. 10, the angle between the axis of all the blades 3 and the axis of the turbine is a right angle, and the axes of the blades 3 intersect at the axis of the turbine. In the case of slots 6 shaped like a basic line segment, the blades 3 may have a front wall 9 and a rear wall 10 defined by substantially a part of the shell of a comical cone. The cones corresponding to the front wall 9 and the rear wall 10 have different axes and / or apex angles and / or their apexes are mutually shifted in the direction of the axis. The blades 3 extend towards their free ends with an absolute dimension measured, for example, in mm. Measured in degrees by the above-mentioned polar coordinate system, the width of the blades 3 with their axis in the slot 6 may be constant over its entire length. As in the turbine with the axis 28 of the blades 3 parallel to the axis Z described above, the width is the dimension approximately perpendicular to both the axis of the blades 3 and their thickness, the thickness being by default the smallest dimension that ensures the sealing of the slot 6 when the blades 3 pass through, and the width is the dimension that ensures the sealing of the sealing chamber 7 when the blades 3 pass through. The lateral edges 11 of the blade 3 therefore approach each other towards the axis of the turbine. Preferably, the shape of the blade 3 is determined by a cone with an apex on the axis Z, so that the two lateral edges 11 intersect on the axis Z when extended.

[0066] Both the outer surface of the rotor 1 and the inner surface of the stator 2 may have the shape of a part of a spherical area and then have a circular shape for the edge of the free end of the blade 3 to be attached to the stator 2. In this embodiment, the slot 6 is perpendicular to the axis Z. Preferably, the slot 6 extends at its end where the free end of the blade 3 passes, so that the blade 3 also has a thicker thickness at the free end to ensure stability. In the remaining part of its length, the thickness of the blade 3 may decrease towards the free end. In this embodiment, the pressurized chamber 4 is surrounded by the rotor 1 towards the axis of the turbine and by the stator 2 in the opposite direction, both faces are also part of the stator 2. The number of blades 3 and therefore the beta (β) angle may also be, for example, as described for the first illustrated embodiment above. In the mounting position, the partition 5 is preferably thickest towards the slot 6 between the parts to provide sufficient strength. As the partition 5 narrows, the slot 6 narrows in the direction of the passage of the blade 3, so that the partition 5 does not impede the continuous movement of the blade 3. The partition wall 5 is attached in its parts to both faces 13 of the pressure chamber 4. In the present embodiment, the blades 3 rotate continuously with the same angular speed as the rotor 1. However, it is also possible to combine this angle of rotation of the axis of the blades 3 with different gear ratios between the rotation of the blades 3 and the rotor 1, and with a swiveling motion or a non-uniformly fast rotary motion.

[0067] In the illustrated embodiment, the gear mechanism with a 1:1 ratio for the rotation of the blades 3 is implemented in such a way that adjacent blades 3 are always pressed into different gears, making the mechanism as small as possible. This mechanism is shown in figures 8 and 9. Figure 8 is a cross-section of the turbine through the plane in which the axes of the turbine and the partition wall 5 lie, thus showing the gear mechanism for a first half of the blade 3, including a series of shafts connected to the blades 3, two auxiliary shafts and a number of teeth. The first auxiliary shaft is rotatably attached to the rotor 1, flowing in the axial direction of the turbine into a toothed chamber 14 through which a space is defined for the movement of the teeth during the rotation of the rotor 1 or for the rotation of the rotor 1 around the toothed gears. The second auxiliary shaft is rotatably attached to the stator 2. As can be seen in figure 8, the shaft of the blade 3 includes a first tooth 15 pressed into a second tooth 16 on the first auxiliary shaft. The other end of this shaft is pressed by its third tooth 17 into the fourth tooth 18, which is rotatably mounted on the stator 2 on the second auxiliary shaft. This shaft is then pressed by its fifth tooth 19 into the sixth tooth 20, which is part of the rotor 1 and is located around the axis of the turbine inside the tooth chamber 14. Thus, as a result of the rotation of the rotor 1, the torque is transmitted from the rotor 1 to the second auxiliary shaft, from the rotor 1 to the first auxiliary shaft and from the rotor 1 to the first half of the blade 3, which is pressed into the common second tooth 16 by the first tooth. The gear ratio of the mechanism is then selected with regard to the space possibilities and requirements for the turbine characteristics by choosing the gear ratio of some of the described teeth. Figure 8 further shows how the blade 3, when passing through the slot 6, tightly abuts the wall of the slot 6, sealing it.

[0068] FIG. 9 shows the gear mechanism of the second half of the blade 3. The cross section of this figure has a plane induced perpendicular to the plane of the cross section of FIG. 8 and passes through the sealing chamber 7. This mechanism comprises an auxiliary shaft for each blade 3, the first tooth 15 on the shaft of the blade 3 being pressed into the seventh tooth 21 on the auxiliary shaft, which is pressed at its opposite end by its eighth tooth 22 into a ninth tooth 23 arranged on the stator 2 around the axis Z. In the embodiment shown, this ninth tooth 23 circumscribes closely the main shaft of the rotor 1. The mechanism of this second half of the blade 3 also ensures the rotation of the blade 3 by the rotation between the rotor 1 and the stator 2, with the same gear ratio as the mechanism described in the previous paragraph. Moreover, in FIG. 9 the sealing of the sealing chamber 7 by the blade 3 is visible and it can be seen how the walls of the sealing chamber 7 follow the replica shape of the edge of the blade 3.

[0069] The pressurized chamber 4 may have a length of, for example, 100° to 135°. The centre of the sealing chamber 7 may be, for example, located at 80° to 100° from the slot 6, preferably at 90° from the slot 6. It is also possible to implement the turbine such that these angles that define the position and size of the chamber are measured relative to the flow direction 29 of the blades, i.e. they are negative. In FIG. 10 the rotation of all the blades of the turbine can be seen, whose centres are 90° from the slot. The flow direction 29 of the blades 3 is in this figure counterclockwise, so that the coordinate system is left-handed. In this figure it can further be seen that adjacent blades 3 have shafts of different lengths, as described above with respect to the gear mechanism. The length of the sealing chamber 7 may be a length with 12 blades 3 in the embodiment shown, for example 40° to 70°, preferably 45° to 60°, for example 50°. It is always selected to be permanently sealed by at least one blade 3, so that its length may be shorter in the case of a higher number of blades 3 and may need to be increased in the case of a lower number of blades 3. In the illustrated embodiment, beta is 15°. For example, the inlet channel 8 is oriented parallel to the partition wall 5 so that it is approximately perpendicular to the blades 3 in the sealed chamber 7, but can be rotated by, for example, ±15°.

[0070] FIG. 11A shows a view of a cone-shaped blade 3, and FIGS. 11B-11D show cross-sections of such a blade in several variants. In FIG. 11B, the blade has a constant thickness along its entire length (total length here means the length of the part of the blade 3 protruding from the rotor 1). In FIG. 11C, the blade narrows towards the free end along the entire protruding length. In FIG. 11D, the blade narrows along most of its length and is provided with an extended reinforcing segment 12 at the free end. A detailed view of this segment is shown in FIG. 11E. In general, the reinforcing segment 12 may have virtually any shape, for example its edges or walls may be rounded to avoid stress concentrations at sharp edges and corners. The reinforcing segment 12 can also be used for blades 3 with a constant thickness. The reinforcing segment 12 may have, for example, at its thickest position, the same thickness as the thickness of the blade 3 immediately next to the rotor 1, which may be, for example, twice the thickness of the blade 3 immediately in front of the reinforcing segment 12. In general, the thickness of the blade 3 and reinforcing segments 12 may be virtually any thickness, and is selected with respect to other design features of the turbine, particularly to avoid excessive deformation of the blade 3 during engagement. Blades 3 having reinforcing segments 12 at locations other than near the free ends, for example midway through the length of the blade 3, are also possible. Blades 3 having multiple reinforcing segments 12 are also possible.

[0071] FIG. 16 shows six schematic views of the partition wall 5, the slot 6, the beginning of the pressure chamber 4 and some blades 3. Between FIGS. 16A) to 16F) the rotor 1 rotates in the flow direction of the blades 3. In FIGS. 16A) to 16F) the rotor 1 rotates less than an angle α. In FIG. 16A) one blade 3 is arranged on its axis in the slot 6. In FIGS. 16B) and 16C) one blade 3 gradually leaves the slot 6. In FIG. 16D) the blade 3 is in the position of exit from the slot 6, where only the trailing edge is in the slot 6 and the following blade 3 enters the slot 6. In FIGS. 16E) and 16F) this blade 3 in question gradually changes its position to be suitable for sealing the sealing chamber 7 and for engagement after leaving the slot 6.

[0072] FIG. 17 shows a similar situation in a view in the direction of axis Z, where the entire pressurization chamber 4 is visible. In FIGS. 17A) to 17D), the rotor 1 again rotates less than the angle α. One of the visible blades 3 is provided with hatching in these views, both on the front wall 9 and on the rear wall 10, and the inlet and outlet of the sealing chamber 7 are shown with dashed lines to facilitate orientation in the views. In FIG. 17A), the blade 3 in question starts to enter the space of the sealing chamber 7 by one of its edges. In FIG. 17B), it has rotated further in a position suitable for engagement. In FIGS. 17C) and 17D, this blade 3 in question may already be engaged, but the previous blade 3 starts to leave the sealing chamber 7 and the following blade 3 approaches it. In FIG. 17C), it can also be seen how the other two blades 3 meet in the slot 6.

[0073] In FIG. 18, the passage of a blade 3 through the sealing chamber 7 is shown in four views perpendicular to the axis Z. One of the blades 3 is again marked with a hatch, which in this view is at the base of the blade 3 where the rotational connection to the rotor 1 is ensured. In the upper part of these views, one can see part of the inlet channel 8 screwed to the stator 2, which leads to the pressurization chamber 4 before the sealing chamber 7 begins. In FIG. 18A), the blade 3 in question starts to enter the sealing chamber 7, in FIG. 18B), it starts sealing and is therefore fully engaged. In FIG. 18C) and FIG. 18D), this blade 3 is still engaged, but the following blade 3 starts to leave the sealing chamber 7.

[0074] For the sake of clarity, in Figures 16 to 18 only the blades 3 are mainly marked with reference numbers and the rotation during the rotation of the rotor 1 (combination of the rotation 1 around axis Z and the axis 28 of the blades 3) is different in each perspective of these figures. Thus, from these three figures the movement of the blades 3 is clearly visible, facilitating the understanding of the operation of this turbine.

[0075] In other embodiments, the angle between the axis 28 of the blade 3 and the axis of the turbine Z may be any angle in the interval from 0 to ±90°. With regard to the choice of this angle, the inclination of the slot 6 with respect to the axis of the turbine may also vary, the shape of the blade 3, in particular the relative mutual inclination of the lateral edges 11, may vary, and the location of the center of the sealing chamber 7 may be modified. In particular, depending on the inclination of the axis of the blade 3, these parameters may vary between the values ​​of the same parameters of the first and second exemplary embodiment. For example, if the angle between the axis 28 of the blade 3 and the axis of the turbine is 45°, then the slot 6 may also be inclined by 45° with respect to the axis of the turbine. The location of the center of the sealing chamber 7 may be intermediate between the center in the first illustrated embodiment and the center in the second illustrated embodiment. The blade 3 widens towards the free end (when measuring the width in mm), but less rapidly than in the second illustrated embodiment. When viewed on the axis Z, the lateral edges 11 of the blade 3 may be inclined so that they intersect on the axis Z. In general, the closer the direction of the axis of the blade 3 is to the direction of the axis of the turbine, the more the lateral edges 11 of the blade 3 may be inclined. The more the cone that defines the shape of the blade 3, and in particular the inclination of the lateral edges 11, approaches a cylindrical shape. In the case of the boundary of this cone, then, is a cylinder of the turbine with the axis 28 of the blade 3 parallel to the axis Z. Furthermore, the center of the sealing chamber 7 may approach the partition wall 5 due to the change in the direction of this axis. The choice of the angle between the axis 28 of the blade 3 and the axis Z may affect whether the faces 13 of the pressurized chamber 4 are both part of the stator 2 or one is part of the rotor 1, and similarly whether the inner and outer peripheral walls are both part of the stator 2, the outer peripheral walls are both part of the stator 2 or one is part of the rotor 1, etc. In any embodiment, the turbine may be a gas turbine and may be equipped with a valve 24 for closing the medium inlet channel 8.

[0076] Five exemplary embodiments of turbines with different rotations of the axes of the blades 3 are shown in Figures 12A-12E. In Figure 12A, the gamma (γ) angle of this rotation is 90 degrees, and the free ends of the blades 3 face each other and the axis Z. In Figure 12E, gamma is also 90 degrees, but the shape of the blades 3 corresponds to the turbine previously described with respect to Figures 4-7. In Figure 12B, the axes of the blades 3 are parallel to the axis Z, as in Figures 1-4. Gamma is therefore either 0 degrees, or 180 degrees. In both Figures 12C and 12D, gamma is 45 degrees, and the blades 3 face each other with their free ends and the axis Z, or away from it, and in both of these embodiments the shape of the blades corresponds to a cone with its apex on the axis Z. [Explanation of symbols]

[0077] 1 - Rotor 2 - Stator 3 - Blade 4 - Pressurized chamber 5 - Partition wall 6 - Slots 7 - Sealing chamber 8 - Inlet Channel 9 - front wall 10 - back wall 11 - Lateral edge 12 - Reinforcement segment 13 - Surface of the pressurized chamber 14 - Toothed chamber 15 - first denticle 16 - second denticle 17 - third denticle 18 - fourth denticle 19 - fifth denticle 20 - sixth denticle 21 - Seventh denticle 22 - 8th denticle 23 - 9th denticle 24 - Valve 25 - Valve cam surface 26 - First Arm 27 - Second Arm 28 - Blade shaft 29 - Blade flow direction

Claims

1. A turbine with rotating blades (3) including a rotor (1) and a stator (2) adapted to rotate about a rotor axis Z, wherein n blades (3) equally spaced about said axis Z project from an outer surface of said rotor (1), each blade (3) rotating about its own axis; Each blade (3) comprises a front wall (9) and a rear wall (10), both of which are curved when viewed along the axis of said blade (3), with the centre of curvature being on the same side from said blade (3), each said blade having two side edges (11); The turbine further comprises a pressurized chamber (4) surrounded by a front surface (13) of the pressurized chamber (4) and a rear surface (13) of the pressurized chamber (4) in both axial directions of the turbine, an inner peripheral wall of the pressurized chamber (4), and an outer peripheral wall of the pressurized chamber (4); the beginning of said pressure chamber (4) is defined by a partition wall (5) in two parts, a slot (6) for said blade (3) to enter said pressure chamber (4) is made between both parts of said partition wall (5) and its shape is adapted to closely mimic the shape of said slot (6) when said blade (3) passes through said slot (6); When each blade (3) is at the exit position from the slot (6), it is located inside the pressurized chamber (4) with one edge of the blade (3) located inside the slot (6), and the succeeding blade (3) is at the entrance position to the slot (6) with the blade (3) located outside the pressurized chamber (4) with one edge of the blade (3) located inside the slot (6); The pressurized chamber (4) has, in the flow direction of the blade (3), first an inlet channel (8) for supplying a medium to the pressurized chamber (4) and then a flow channel (4) having a flow rate of at least α, but [0010] a sealing chamber (7) having a length of 0.01 mm, the center of the sealing chamber (7) being located away from the slot (6) in the flow direction of the blade (3) in the range of +65° to +100° or -65°; 10. The turbine as described above, characterized in that at each position of rotation of the rotor (1), the slot (6) is sealed by at least one blade (3) and the sealing chamber (7) is sealed by at least one other blade.

2. 2. Turbine with rotating blades (3) according to claim 1, characterized in that the number n of the blades (3) is between 5 and 100.

3. 10. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that the turbine comprises m pressurised chambers (4), each comprising a sealing chamber (7), a partition wall (5), a slot (6) and an inlet channel (8), where m is an integer between 1 and 10.

4. 4. A turbine with rotating blades (3) according to claim 3, characterized in that the blades (3) are adapted to rotate about their own axis using a gear ratio of m:1 to the rotational speed of the rotor (1).

5. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that the turbine is selected from the group consisting of a water turbine, a steam turbine or a gas turbine.

6. 10. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that each blade (3) has its own plane of symmetry in which the axis of said blade (3) lies, and when said blade (3) is located in the centre of said sealing chamber (7), said axis of said inlet channel (8) forms an angle of less than 15° with said plane of symmetry of said blade (3).

7. 10. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that the blades (3) are adapted to rotate with an angular velocity equal to an integer multiple of the angular velocity of the rotor (1).

8. A turbine equipped with a rotating blade (3) according to any one of claims 1 to 6, characterized in that the blade (3) is adapted for oscillating rotation.

9. 10. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that each blade (3) is provided at its free end with a reinforcing segment (12) of increased thickness.

10. 10. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that the thickness of each blade (3) decreases over the majority of the length of said blade (3) towards its free end.

11. 10. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that the shape of the sealing chamber (7) is defined by the envelope of the compound movement of the edges of the blades (3) passing through the sealing chamber (7).

12. 10. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that the shape of the front wall (9) and the rear wall (10) of each blade (3) is defined by the envelope of the combined motion of the blade (3) relative to the slot (6) and through the slot (6).

13. 10. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that the axes of the blades (3) are parallel to the axis of the turbine, the centres of the sealing chambers (7) are located at a distance from the slots (6) along the flow direction of the blades (3) in the range of 65° to 85° or -85° to -65°, and the lateral edges (11) of each blade (3) are parallel to the axis of the blades (3).

14. A turbine with rotating blades (3) according to any one of claims 1 to 12, characterized in that the axis of the blades (3) is perpendicular to the axis of the turbine, the centres of the sealing chambers (7) are located away from the slots (6) within a range of 80° to 100° or -100° to -80° in the flow direction of the blades (3), and the side edges (11) of each blade (3) are close to each other in the direction of the axis of the turbine.

15. A turbine with a rotating blade (3) according to any one of claims 1 to 12, characterized in that the angle of rotation of the axis of the blade (3) relative to the axis of the turbine is selected from the closed interval from -90° to 90°.

16. 10. A turbine with rotating blades (3) according to any one of the preceding claims, characterized in that the turbine is designed for gaseous media and the inlet channel (8) comprises a valve (24) adapted to each blade (3), opening the inlet channel (8) after the given blade (3) has entered the sealing chamber (7) and closing the inlet channel (8) after a maximum of 0.6α rotations of the rotor (1) since the inlet channel was opened.

Images