FR2880382A1 - Turbomachine, has blades performing double rotation, maintaining fixed orientation with respect to stator, and placed at regular intervals on rotor, so that behavior of chambers with variable volume remains uniform - Google Patents

Abstract

The turbomachine has a stator (1) with outer and inner walls delimiting a channel (4) whose width increases based on position of blades (5) with respect to central axis. The blades perform double rotation and maintain fixed orientation with respect to the stator. The blades are placed at regular intervals on a rotor, so that behavior of chambers with variable volume remains uniform. An independent claim is also included for a compression device based on the turbomachines including two turbomachines placed in series.

Description

Turbomachine with paddles

  The present invention relates to a turbomachine with blades for ensuring an energy exchange between a flowing fluid and a rotor driven by a rotational movement on which said blades are disposed. This turbomachine operates with a closed chamber provided with at least one inlet opening and at least one outlet opening to ensure the flow of the fluid involved in the energy exchange.

  The turbomachine of the invention can operate as a generator, when it communicates energy to the fluid, and that its rotor is rotated for example by an external motor: the blades then transfer fluid energy. The same goes for the same when the turbomachine itself operates as a motor.

  Conversely, it can operate as a receiver, that is to say a turbine, when it receives energy from the fluid, which energy is then transmitted back to the rotor. In principle, the energy imparted to the fluid in the generating version leads to an increase of its pressure, whereas the energy borrowing, when it is the fluid that is used as the primary vector of the energy in a use in turbine, is usually accompanied by a decrease in pressure.

  The object of the present invention is to provide a turbomachine having a very high efficiency, in a use both generator and turbine, which implies that the energy losses are, in the structure that has been developed, reduced to a minimum.

  In other words, when the turbomachine communicates fluid energy, and that it operates as a generator or directly engine, the problem is to minimize mechanical losses and simultaneously ensure a high compression ratio. In the operating turbine receiver, when the fluid communicates its energy to the mechanical system, the concern is to provide a mechanical system that, unlike many current turbines, retains the pressure to increase efficiency.

  In order to fulfill these objectives, the turbomachine of the invention is essentially characterized in that: the blades rotate with the rotor; each blade is free to rotate with respect to the rotor along a central axis parallel to the axis of rotation of the rotor; the blades are identical and their axes are arranged in a circle; the vanes maintain a fixed orientation with respect to the stator; 2880382 2 they are connected by a device for synchronizing their rotation with respect to the rotor; and the stator has inner and outer walls parallel to the axes of rotation, which constitute the side walls of a passage passage for the blades, said side walls being drawn in such a way that they are each in constant contact with all the blades which permanently obstruct said corridor.

  In this configuration, the blades thus maintain the same orientation with respect to the stator, whatever the position they occupy when they rotate around the central axis (axis of rotation of the rotor) of the turbomachine, in a closed configuration provided to guarantee an optimal maintenance of the internal pressure by creation between the blades of interior chambers of variable volume.

  The inertia of the mechanical system is reduced, in particular because of the double rotation of the blades, which each constitute an independent and smaller mechanical system which, with regard to the connections, the relative displacements, the leaks, the sealing, etc. .. is much easier to control than a single rotating structure submitted, especially at high power, to significant mechanical stress.

  Preferably, the vanes are arranged inside the stator at regular intervals on the rotor. The behavior of the variable volume chambers, during compression or expansion of the fluid according to the uses and / or the positions of the blades, remains uniform and allows a regularity of operation favorable to a good mechanical strength of the system.

  According to a first variant of the invention, the rotor of the turbomachine of the invention comprises two plates between which are disposed the inner and outer walls of the stator, the assembly defining the passage passage of the blades, which are connected to said plates.

  According to a second variant, the rotor comprises a single plate constituting one of the upper or lower walls of the passage of the blades, the other of these walls being secured to the stator.

  The side walls of the stator, which participate by their shape in the objective of improving the tightness of the assembly, have a pattern that depends on the shape given to the blades and is similar to two distinct ellipses, one being integrated into the other. This shape makes it possible at any moment for the blades, whatever their position, to obstruct the corridor delimited on the one hand by the walls of the stator and on the other hand by at least one rotor plate and, if appropriate, a plate of the stator. This construction allows the production of compression or expansion chambers directly between two successive blades of the 2880382 3 turbomachine, and promotes the compression or expansion operation with maximum efficiency at least in the areas in which the chambers thus defined n ' do not interfere with fluid inlet and outlet openings. These are also positioned according to the use that we want to have the turbomachine.

  The tightness is further enhanced, especially between the rotor plate (s) and the stator walls, by the existence of flexible segments that do not interfere with the displacement of the blades with respect to the stator, but contribute to effectively partitioning each chamber. compression or expansion of variable volume.

  According to the invention, the blades are preferably provided at each adjacent axial end of a rotor plate, a disk embedded in the volume of said plate, preferably flush with its surface, and free to rotate relative to said plate.

  This mechanical characteristic also makes it possible to improve the mechanical efficiency of the system, by minimizing the friction losses, without affecting the efficiency of the compression or expansion operations of the fluid, since the discs do not encroach on the volume of the internal passageway. . In the case of a rotor with a single plate, the ends of the blades opposite to the latter slide in contact with a flat surface integral with the stator.

  To further optimize the mechanical connections, said discs are connected to the (x) plate (x) of the rotor by means of a bearing for example ball or bearings.

  Each mechanical connection is in fact designed in the sense of a reduction of the resistant forces in order to reduce the mechanical yield losses at each step.

  As in the connection between the rotor plates and the stator walls, the sealing between the blade discs and each rotor plate is achieved by means of flexible annular segments to isolate the fluid in the variable volume chambers during compression or relaxation operations. Alternatively, the seal can be made between the discs or the trees protruding blades and each plate, using lip seals.

  As has been mentioned before, one of the fundamental aspects of the turbomachine of the invention lies in the synchronization of the rotation of the blades when they rotate relative to the rotor. From a mechanical point of view, this synchronization is based in particular on the existence, at at least one end of each blade, of a central shaft for connection to a device for synchronizing speed and position of said blades.

  The rotor, driven by a clean rotation movement, is therefore provided with complementary elements enabling it to manage the rotation of each blade, in the form of at least one synchronization device.

  More specifically, according to one possibility, each synchronization device comprises a plurality of disks or synchronizing arms each attached to a central blade connection shaft, and provided with a radially outwardly offset journal, the assembly journals driving a synchronizing plate rotating about a pivot protruding from the stator, which has, with respect to the axis of rotation of the rotor, the same offset as that of the journals relative to the axis of rotation of the blades, said pivot and said journals being free in rotation in the synchronization plate.

  The synchronization plate (s) actually guides the movement of the blades and is or are located outside the rotor / stator block.

  Preferably, the blades have a section of elliptical shape comprising a large axis of length much greater than that of the minor axis, and move in a corridor in the form of two symmetrical croissants joining in two connecting necks of width substantially equal to small axis.

  The shape of said corridors obviously depends closely on that of the blades, since they are in constant contact with the two side walls, and they also keep more permanently the same orientation with respect to said walls.

  Spacers positioned and dimensioned respectively to cross adjusted the connecting necks are disposed between the blades, said spacers being secured to each plate of the rotor and of equal length to that of the blades.

  According to one possibility, an inlet opening and an outlet opening are made in the stator for each crescent portion of the corridor.

  Such a configuration may for example be applied to a steam turbine, or to a compressor, depending on whether the use of the turbomachine is in the receiver or generator.

  The fluid currents in each crescent are then obviously oriented so that they allow rotation of the rotor in the turbine.

  In the same logic of sealing as before, it is possible to provide the radial edges of the vanes of sealing segments.

  It should be noted that these segments, the use of which may be required or advised in certain types of use, may also be omitted in other applications.

  The turbomachines of the invention can also be configured as a motor, when one of the walls of the stator is equipped with a fuel injector disposed near a spark-type ignition device.

  In this case, it is of course necessary to provide the positioning of the injector and the candle in a section of the corridor corresponding to an internal combustion chamber in which the pressure is high. The arrangement of the inlet and outlet openings is then such that the supply fluid can be properly compressed, and that the exhaust is in the same way possible in good conditions.

  It is obviously possible to associate such a motor with a turbomachine of the invention arranged upstream, to achieve a pre-compression of the oxidizing fluid.

  In the case of the aforementioned double-increasing configuration, the fuel injector and the contiguous ignition device are located near a connecting neck, intake and exhaust openings being provided on both sides. other and in the vicinity of the other neck.

  In general, the invention relates, in addition to the turbomachines themselves, compression devices which are characterized in that they comprise at least two turbomachines arranged in series. This configuration in successive stages of compression allows a gradual increase in pressure, according to the principle of an aircraft reactor.

  Of course, the number of blades, as well as their dimensions, are variable depending on the use and the size of the turbomachine. In general, the design of the turbomachine of the invention allows the implementation of multiple variants according to the applications envisaged, as well as the use of a wide range of materials of all kinds to manufacture its various components.

  Among others, we can mention plastic, steel, tungsten, carbon, refractory materials, etc ... the choice being made according to the constraints of use (lightness, power, nature of the fluid, etc.).

  ). The use of all these materials is especially made possible by the absence of micro kinetic shocks, including resistance to inertia, hence the possibility of using heavy parts at high speed, including supersonic ... DTD The uses of such a turbomachine are obviously extremely numerous, the high efficiency it offers constituting an important advantage. For the record, we can mention the use of steam turbine, which allows operation at lower pressures than current turbines to obtain an equivalent performance.

  2880382 6 The energy gain is obvious, opening the possibility of using smaller installations, and therefore more economical than current installations for equivalent uses.

  The turbomachines of the invention also make it possible to recover energy in gas furnaces, or any other fuel furnace, for example to transform the lost mechanical energy into electrical energy.

  Air compressors are also a possible application, the air friction between moving and fixed parts being reduced, which implies, for an identical yield, kinetic energy losses and lower noise, and therefore a decrease of energy consumption.

  Mention may also be made of the use of the turbomachines of the invention in jet engines, or other engines, in which they notably provide an appreciable gain in terms of compression. Once again, because of the high efficiency, the compression allowed by the turbomachines of the invention is obtained at lower rotation, that is to say with less fuel and less energy loss. At equal power, the engines usable are much lighter, achievable at a lower cost, and they finally cause reduced pollution.

  In the field of pumps, the excellent sealing of the machine of the invention allows efficient suction, especially in suction pumps.

  The advantages of the invention are therefore numerous and considerable. The invention will now be described in more detail with reference to the appended figures for which: FIG. 1 is a partial perspective view of a turbomachine according to the invention; - Figure 2 shows, in transversely sectioned perspective, the mechanical structure of the turbomachine; - Figure 3 shows the association of the rotor with the blades; FIG. 4 shows the insertion of the group of FIG. 3 into a stator; - Figure 5 completes the device of Figure 4 by adding a fixed plate of the rotor; and FIG. 6 shows the addition of an external synchronization plate.

  With reference to FIG. 1, the stator (1) comprises an outer wall (2) and an inner wall (3) which delimit a corridor (4) whose width changes as a function of the position of the vanes (5) with respect to a central axis (A).

  The turbomachine shown in FIG. 1 is a motor, and the stator (1) therefore comprises a fluid supply duct (6) and an exhaust duct (7) which cooperate with corresponding openings in the outer wall ( 2) the stator. Opposite these ducts (6, 7) is an injector (8) and an ignition device (9), for example a spark plug, which allow motor operation.

  The blades (5) are in free rotation connection with the rotor, and more particularly with at least one plate (11) integral with this rotor. The blades (5) keep, during their rotation relative to the axis (A), always the same orientation. They are in permanent contact with the two outer side walls (2) and the inner side of the stator (1), the latter delimiting a central block (3).

  The shape that is given to each blade (5), in this case an elliptical shape with a small axis of length much shorter than that of the major axis, induces a shape of the corridor (4) in two croissants separated by necks whose width is substantially equal to the length of the minor axis.

  Spacers (12), whose functions will be explained in more detail below, are secured to the plate (11) of the rotor between the vanes (5). The ends of the blades (5) are provided with studs (13) for including the fixing of a disc (14) free end rotated in a housing provided for this purpose in the plate (11).

  Referring now to FIG. 2, the turbomachine shown comprises a rotor with two plates (11, 11 ') each comprising housings receiving discs (14, 14') fitted to the two ends of each blade (5).

  The section that appears in Figure 2 is actually not performed parallel to the axis (A). The cutting planes have indeed a slight angle with respect to this axis (A), which explains why the vanes (5) appearing are cut in a trapezium.

  The blade (5) on the right shows that, whatever its position relative to the stator (1), each blade (5) obstructs the entire section of the corridor (4) in which it moves. The housings receiving the disks (14) may comprise a central recess (15) intended to contain a ball bearing or equivalent (pad) for facilitating the rotation of each blade (5) relative to the plates (11, 11 ') of the rotor .

  The stator (1) comprises, in its inner wall (3) as well as in its outer wall (2), grooves respectively referenced (16, 17) provided for housing seals. The pads (13) protruding blades (5) extend beyond the end discs (14), and pass through orifices (18) formed in the plates (11, 11 ') of the rotor.

  Other disks (19), as shown in FIG. 3, can be secured to said pads (13), so as to result in a superposition of disks (14 ', 19). For the sake of clarity, this FIG. 3 only shows one part of the rotor: only one plate (11) is shown with a certain number of vanes (5). Of these blades (5), only some are in turn provided with disks (19). In principle, a second plate (11 ') is inserted between the discs (14) and (19). In this figure, only part of the inner block (3) of the stator appears.

  The discs (19) serve to synchronize the movement of the blades (5) relative to the rotor. Thus, it has been reported that these vanes (5), although rotating around the axis (A) in the stator, maintain a fixed orientation with respect to this stator (1). They are therefore rotatable relative to the rotor, and more particularly relative to the plates (11, 11 ') of this rotor.

  It is therefore appropriate that said rotation is controlled and maintained equal for all the vanes (5) so that they can maintain their fixed orientation relative to the stator (1).

  For this purpose, each synchronization disc (19) is provided with a journal (20) offset on the periphery of this disc. Similarly, the central portion of the stator (1) is provided with a pivot (21). The offset between the axis of this pivot (21) and the axis (A) is identical to the offset between the axis of the trunnions (20) and the axes of rotation (B) of the vanes (5).

  Returning to Figure 2, there is the existence of a plate (22) synchronization having, at its periphery, a number of orifices (23) regularly distributed, and a central orifice (24). These orifices respectively receive the pins (20) and the pivot (21) in a freely rotatable connection.

  Figure 4 shows the group of Figure 3 inserted into the stator. To improve the understanding of the system, Figures 3 and 4 have been shown without the rotor plate (11 ') although in the illustrated configuration this plate (11') is functionally necessary.

  Figure 4 also reveals the existence of axial grooves (25, 25 ') for improving the sealing at the neck separating the two crescent parts of the corridor (4). The configuration shown in FIG. 4 is no longer a motor, but a turbine or a compressor, depending on its use as a generator or receiver, which consequently comprises inlet and outlet openings (26, 27) for each crescent of the corridor (4).

  The spacers (12) have an obvious stiffening function, for example in a two-plate rotor configuration (11, 11 '). However, they also have a sealing function, especially when they pass the bottleneck separating the two crescent parts of the corridor (4). Their size corresponds to this effect to the width of said necks.

  Finally, particularly in these throttling areas, they help direct the fluid to the outlets, or from the inlets to the vanes (5).

  FIG. 5 shows a turbomachine configuration according to the invention with a two-plate rotor (11, 11 '), that is to say that the view 4 has been completed so that the plate (11') also appears and all of the sync disks (19).

  Finally, the synchronization plate (22) has been added in FIG. 6, which represents a turbomachine configuration in a compressor or a turbine provided with a device for synchronizing or guiding the vanes (5) as described above.

  A variant of this machine equipped with a single plate (11) would be quite possible to implement, the wall of the corridor (4) hitherto provided by the other plate (11 ') of the rotor being then made by a plate integral with the stator (1).

  Similarly, it would also be possible to envisage a variant in which the synchronization plate (28) comprises a symmetrical plate on the other side of the turbomachine.

  The turbomachine thus described is integrated in a housing.

  The examples which have been illustrated by the figures above are of course not to be considered as being exhaustive of the invention. It encompasses all the variants of shape and configuration that are within the reach of those skilled in the art.

Claims (17)

  1. Turbine engine with vanes (5) arranged on a rotor cooperating with a stator (1) comprising at least one inlet opening (6) and an outlet opening (7) of the fluid, said vanes (5) moving in a space defined by the stator (1) and the rotor, characterized in that: the vanes (5) rotate with the rotor; each blade (5) is free to rotate with respect to the rotor along a central axis (A) parallel to the axis of rotation of the rotor; the blades (5) are identical and their axes are arranged in a circle; the vanes (5) maintain a fixed orientation with respect to the stator (1); they are connected by a device for synchronizing their rotation with respect to the rotor; and - the stator (1) has inner (3) and outer (2) walls parallel to the axes of rotation, which constitute the side walls of a passage (4) for the vanes (5), said lateral walls being plotted so that they are each in constant contact with all the vanes (5), which permanently obstruct said passage (4).   2. Turbomachine according to claim 1, characterized in that the blades (5) are arranged at regular intervals on the rotor.   3. The turbomachine according to one of claims 1 and 2, characterized in that the rotor comprises two plates (11, 11 ') between which are disposed the inner walls (3) and outer (2) of the stator (1), the assembly defining the passage (4) for passage of the blades (5), which are then connected to said plates (11, 11 ').   4. Turbine engine according to one of claims 1 and 2, characterized in that the rotor comprises a plate (11) constituting one of the upper or lower walls of the passage (4) of the blades (5), the other these walls being secured to the stator (1).   5. Turbomachine according to one of claims 3 and 4, characterized in that the seal between the or plates (11, 11 ') of the rotor and the walls (2, 3) of the stator (1) is made to help with flexible segments.   6. Turbomachine according to one of claims 3 to 5, characterized in that each blade (5) is provided at each of its axial ends adjacent to a plate (11, 11 ') of the rotor, a disk ( 14, 14 ') embedded in the volume of said plate (11, 11') and flush with its surface, free to rotate relative to said plate (11, 11 ').   7. Turbomachine according to the preceding claim, characterized in that each disc (14, 14 ') is connected to the plate (11, 11') of the rotor by means of a bearing for example ball or bearings.   8. Turbine engine according to one of claims 6 and 7, characterized in that the seal between the discs (14, 14 ') of the blades (5) and each plate (11, 11') of the rotor is made to the using flexible ring segments.   9. Turbomachine according to one of claims 6 and 7, characterized in that the seal between the discs (14, 14 ') or the shafts (13) protruding from the blades and each plate (11, 11') of the rotor is made using lip seals.   10. The turbomachine according to one of claims 6 to 9, characterized in that at least one end of each blade (5) is provided with a central shaft (13) for connection to a gear synchronization device. and positions of the blades (5).   11. Turbomachine according to the preceding claim, characterized in that each synchronization device comprises a plurality of disks (19) or synchronizing arms each fixed to a central shaft (13) for connecting a blade (5), and provided with a journal (20) offset radially outwardly, the assembly of the journals (20) driving a synchronization plate (22) rotating around a pivot (21) protruding from the stator (1), which, by relative to the axis (A) of rotation of the rotor, the same offset as that of the journals (20) relative to the axis of rotation of the vanes (5), said pivot (21) and said journals (20) being free in rotation in the synchronization plate (22).   12. Turbomachine according to any one of the preceding claims, characterized in that the blades (5) have an elliptical-shaped section comprising a major axis of length much greater than that of the minor axis, and move in a corridor (4). ) in the form of two symmetrical croissants joining in two connecting necks of width substantially equal to the minor axis.   13. Turbomachine according to the preceding claim, characterized in that spacers (12) positioned and dimensioned respectively to cross fit the connecting necks are arranged between the blades (5), said spacers (12) being secured to each plate (11, 11 ') of the rotor and of equal length to that of the vanes (5).   Turbine engine according to one of Claims 12 and 13, characterized in that an inlet opening (26) and an outlet opening (27) are formed in the stator (1) for each crescent portion of the passage ( 4).   15. Turbomachine according to any one of the preceding claims, characterized in that the radial edges of the blades (5) are provided with sealing rings.   6. A turbomachine according to any one of the preceding claims, characterized in that one of the walls (2) of the stator (1) is equipped with a fuel injector (8) arranged near a device ignition (9) candle type.   17. A turbomachine according to claim 12, characterized in that a contiguous fuel injector (8) and ignition device (9) are located near a connecting neck, inlet openings (6) and exhaust (7) being provided on both sides and in the vicinity of the other neck.   18. A compression device based on turbomachines according to the preceding claims, characterized in that it comprises at least two turbomachines arranged in series.