• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Shown are a rotor (1) and a radially flow-through turbine, in particular micro gas turbine, which has a shaft (3) and one or more, then parallel to each other, discs (4), wherein on the outer periphery of the discs outwardly directed outer blades (6 ) are arranged. In order to utilize the remaining energy in the flow when it leaves the disk region of the rotor, it is provided that the disks (4) between outer periphery and shaft (3) have at least one recess within which inner moving blades (7) are provided.
    公开号:AT512653A4
    申请号:T7242012
    申请日:2012-06-28
    公开日:2013-10-15
    发明作者:
    申请人:Kares；
    IPC主号:
    专利说明:

    ·· ♦ · · · · · · · · · - * ♦ * ·· * Φ II · I Μ · 1 * · · · · I
    RUNNERS AND RADIAL RUNNING TURBINE
    FIELD OF THE INVENTION
    The invention relates to a rotor for a radially durchströmbare turbine, in particular micro gas turbine having a shaft and one or more, then arranged parallel to each other, discs, wherein on the outer periphery of the discs outwardly directed outer blades are arranged, and a corresponding turbine.
    A turbine represents a fluid energy machine in which the energy contained in a supplied fluid (liquids and gases) is converted into rotational energy. As the fluid flows through the turbine, the energy is delivered to the turbine and the rotational energy of the rotating turbine is delivered to a work machine, such as a generator for generating electrical power. Generally, the turbine and work machine (e.g., the generator) are interconnected via their respective rotatably supported shafts.
    Gas turbines are operating on the principle of flow combustion engines. They combine the advantages of turbomachinery with those of "internal combustion engines". Gas turbines are electric generators, pumps, compressors,
    Ships ships, aircraft, helicopters and motor vehicles.
    Micro gas turbines are small gas turbines that have low combustion chamber pressures and combustion chamber temperatures. The power of these turbines is less than 250 kW.
    The subject turbines are flowed through radially, that is, the fluid flows to transmit energy radially from outside to inside through the turbine, so normal to the axis of rotation of the shaft. The discs are circular, usually flat and rigid and have a constant thickness. They are usually arranged normal to the shaft.
    STATE OF THE ART
    The present invention is based on the patents US 1 061 206 A and US 1 061 142 A, both to Nikola Tesla. From the patent US 1 061 206, there is known a disc rotor turbine, also referred to as a Tesla turbine, in which a rotor is used, on which a multiplicity of discs are arranged, whereby a blade-free rotor is provided • Ml ·· »· Μ ·· · Ί · · «··· Ο · ·« Μ | · «* Γ · Μ ·« I ·
    * · «· I I · t · I is formed. Tesla itself has expanded its original concept, which can be seen in the publications GB 174 544 A and GB 186 082 A.
    Other developments have relied on the Tesla concept of the friction turbine, but none of the turbines in the following publications have yet found widespread implementation or commercial use. A common disadvantage of the previous solutions is their low efficiency compared to other turbines in the same power class.
    US 2007/0296219 A1 describes an arrangement of stator and rotor for a wind turbine. An attempt was made to adapt the Tesla turbine for use as a wind turbine. The rotor has according to the preamble of claim 1 on the outer periphery of the disc stack blades.
    WO 2008/070369 A2 describes a wind turbine, which can also be used as a steam turbine, and also takes over the basic Tesla concept. The individual discs are spaced within the outer circumference by spacers having a wing profile. US 2003/0053909 A1 describes a rotor arrangement for a radial turbine, where aerodynamic profiles extend between the outer and inner edges of the respective disk. WO 2009/109020 A1 describes a modified rotor of the Tesla turbine, the whole arrangement being called "hybrid Tesla-Pelton disc turbine" because the disks of the rotor are not flat, but have recesses similar to the blades in Pelton turbines ,
    From DE 10 2009 047 942 A1 a Tesla turbine with a rotor is known which has a shaft with a hollow section in order to improve the flow conditions.
    Another publication where it is attempted to apply and improve the concept of the Tesla turbine is US 2002/0182054 A1. In order to avoid the chamfering of the end disks of the rotor, a stepwise arrangement of disks of different diameters is proposed here.
    PRESENTATION OF THE INVENTION
    An object of the present invention is to design a rotor and a housing including tail for a micro gas turbine in such a way that the efficiency of the entire arrangement is improved with respect to currently available turbines of this power class. MM · *
    According to the invention this object is achieved by a rotor for a radially through-flow turbine, such as a radial Reibungsmikrogasturbine, according to the features of claim 1 or by a turbine according to claim 12. In the dependent claims further embodiments of the present invention are given.
    When rotor according to claim 1 it is provided that the discs - seen in the radial direction - between the outer periphery and shaft have at least one recess, within which inner blades are provided. This allows the residual energy in the flow to be utilized as it leaves the disk area of the rotor. This series formed from the inner blades should, as usual in a "cantilever type turbine", be carried out as a constant pressure stage.
    Very easily, the recesses according to the invention can be realized in that the discs have the shape of a circular ring to form a recess and the inner blades are arranged within the inner circumference of the discs.
    If the inner blades are spaced apart from the disks, then, as seen in the radial direction, vanes may be disposed between the disks and the inner blades, such as are attached to the casing of the turbine to direct the flow to the inner blades ,
    The ratio of the outer to the inner radius of the discs is preferably between 1.1 and 3. It is selected depending on the required power from the disc part of the rotor, wherein a larger ratio corresponds to a larger power.
    If the disks have flat surfaces, ie, do not contain any internals such as ribs, depressions or additional blades, then the path of the fluid through the disks (along the disk surfaces) will be dependent on the difference between the speed of the disks and the inlet velocity of the fluid. This also results in a partial load operation of the turbine, a better efficiency than for runners with internals on the discs when the internals are designed for full load operation.
    One embodiment provides that the disks - as seen in the axial direction - are arranged between at least partially disc-shaped end elements. These termination elements are usually stronger, about thicker, designed as the discs and can serve to attach the discs. They can also be designed as circular rings. They are usually wider in the radial direction than the discs in order to attach about as well as the outer blades can. The space between the first and the last slice on the one hand and the adjacent closure element on the other hand • * * · * «• ·« · * · · ««
    is also traversed by the fluid. Thus, the runner could also have only one disc and two end elements. Most of the runner but has several discs. By varying the number of disks can be made an adjustment of the performance of the rotor or the turbine. Depending on the number of slices then the other elements must be adjusted, such as the height of the blades and vanes.
    The end elements may have on their side facing away from the discs a plurality of concentric recesses. These can cooperate with corresponding elevations of the housing according to the principle of a labyrinth seal.
    It can be provided that the vertical axis of the outer and / or the inner rotor blades forms an angle with the axis of rotation of the shaft. This results in better running smoothness and less noise. The preferred angular range is between 0® and 20®.
    The blades are particularly easy to manufacture when the inner and outer blades have the same cross-section over their entire height. This applies both to blades whose vertical axis is parallel to the axis of rotation, as well as for those whose vertical axis forms an angle with the axis of rotation of the shaft.
    If the outer blades are aerodynamically shaped, then the dynamic buoyancy of the blades can be used to drive the rotor.
    In order to increase the mechanical stability of the rotor, it can be provided that the trailing edges of the outer rotor blades have recesses in which the outer edges of the disks - in particular a form-fitting - are inserted. At the same time, the individual rotor blades thus also assume the function of the peripheral spacer elements for the disks.
    In principle, however, the outer blades could also be arranged at a distance from the discs.
    The inventive radially durchströmbare turbine, in particular micro gas turbine, comprising ai runner according to the invention and a housing with a bearing for the shaft of the rotor, wherein the housing surrounds the rotor and an area in an inflow leading inlet opening and a fluid outlet, characterized in that Housing outer vanes, which are arranged outside of the outer rotor blades of the rotor. The outer vanes serve to increase the kinetic energy of the fluid. For example, the same number of outer dimensions can be used. * * * «• 99 * 9 ·« · ♦ · «
    Guide vanes such as outer blades may be provided so that each outer vane directs the fluid to an outer rotor blade
    The housing may further include inner vanes disposed radially between the inner rotor and the discs. These additionally increase the kinetic energy of the fluid. The number of inner vanes may be less than the number of inner vanes to minimize losses.
    The housing may further - on the inside, opposite the Abschiussei of the rotor - have several concentric ridges which protrude into the recesses of the end elements of the rotor to realize a labyrinth seal.
    If the inner and outer vanes have the same cross-section over their entire height, the cross-section being delimited by straight lines, then the vanes can be made particularly easily.
    With the present invention, the following advantages are achieved;
    It is an efficient conversion of the fluid flow of the fluid allows, because of different methods (boundary layer phenomena, conservation of momentum, buoyancy) are used. The Tesla Tobacco Approach will be expanded and improved.
    The turbine according to the invention can be realized economically by the simple mechanical construction and inexpensive heat-resistant alloys. The manufacturing costs and operating costs are lower than for currently available products of comparable performance, including the possibly two-dimensional geometry of the blades (same cross-section over the height) and the simple two-dimensional geometry (without buckling) of the vanes. An elaborate cooling and associated Hiifssysteme can be dispensed with.
    The rotor of the present invention has increased structural strength relative to previous designs of the Tesla shovelless turbine.
    Examples of fields of application of the invention are combined heat and power plants and range extender aggregates in motor vehicles. Of course, this does not exhaust all possible uses, such as Turbocharger for piston engines or Auxiliary Power Units (APU) for aircraft, etc.
    The turbine of the present invention is preferably used as a gas turbine, use as a steam turbine would also be possible. The rotor would be basically at
    Replaceable wind turbines, however, the turbine requires high velocities of the fluid> 100m / s, which is unlikely to be achieved with the usual prevailing wind.
    BRIEF DESCRIPTION OF THE FIGURES
    The invention will be explained with reference to an example to which further advantageous embodiments of the invention can be taken. It shows
    1 shows the axial cross section through a turbine according to the invention,
    2 shows the radial cross section (along the line A - A ') through the turbine of FIG. 1, FIG. 3 shows the axial cross section through the rotor of FIG. 1,
    4 shows the axial cross section through the housing of FIG. 1,
    Fig. 5 is an outer blade in plan and side view.
    WAYS FOR CARRYING OUT THE INVENTION
    The radial friction micro-gas turbine according to the present invention comprises a multi-part housing 2 and a rotor 1, see FIG. 2.
    The rotor 1 according to FIG. 1 comprises a rotatably mounted shaft 3, which is connected in a predetermined region to a lower end element 13 and a row of rotationally symmetrically arranged inner rotor blades 7 by means of first connecting elements 15. The connecting elements 15 can preferably be designed as screws. The attachment is such that when force is applied to the discs 4, this force can be transmitted as torque to the shaft 3. In the direction of the fluid outlet 16, the shaft 3 ends in a flow-guiding element 17. The shaft 3 tapers in the region of the inner rotor blades 7, in the direction of the fluid outlet 16, that is to say in FIG. Fluid exiting the inner rotor blades 7 can flow to the fluid outlet 16 with minimized losses in the free space thus formed. The other end of the shaft 3 can be connected to an electric generator, which has not been shown in the present figures.
    It is the bottom and the upper end elements (end plates) 13, 5 to distinguish. The discs 4 are formed as substantially annular flat discs, and are in the form of a stack between the lower end member 13 and the upper, designed as an annular end disc 5 Abschuusselement parallel to each other: r * 7u. arranged such that, in conjunction with spacer elements 18, which are each arranged between adjacent disks 4, the disks 4 have a predetermined distance from each other. The predetermined distance between the respective disks 4 is thus determined essentially by the dimensions of the respective spacer element 18. Thus, gaps between the discs 4 are formed. In this way, the predetermined distance can be clearly defined and adhered to during manufacture. The inflowing fluid is directed tangentially in the direction of the plurality of disks 4 and flows in a flow path from the outer edge of the disks 4 into the spaces 19 between the disks 4 (and also between the disks 4 and the end elements 5, 13) in the direction of the inner ones Guide vanes 12. The spacer elements 18, inner discs 4 and the Abschlusslemente 5 and 13 are connected to the second connecting elements 20. The connecting element 20 may be formed as a rod or threaded rod and secured at both ends with Muttem 21, but other embodiments of the connection and attachment are possible.
    The two end elements 5, 13 define the entire stack of disks 4. The two end elements 5, 13 each consist of an annular disc, the lower end member 13 also has a subsequent to the inner periphery of the disc stepped portion, with which the End element 13 can be connected to the shaft 3. For mechanical reasons, the end members 5, 13 are thicker than the inner discs 4. The upper end member 5 has the same inner diameter as the discs 4. Thus, the inner vanes 12, which are secured to the top of the housing 2, project into the rotor 1 ,
    Both the upper end plate 5 and the lower end element 13 is connected to the outer plates 6 and the second connecting elements 20 with the discs 4 by means of the third connecting elements 22, which are designed approximately as screws. Furthermore, the lower end member 13 is connected to the first connecting members 15 with the shaft 3 and the inner blades 7. Both the disc-shaped part of the lower 13 and the upper end member 5 has on the outward (direction housing 2) directed surface concentric shapes, in conjunction with the corresponding shapes on the opposite housing parts 8, 9 - the principle of labyrinth seals following - have the function of reducing leakage losses.
    The so-called outer race is formed from a plurality of outer blades 6, which are usually arranged at the same distance from the shaft 3 and rotationally symmetrical to this. The outer blades 6 begin at the outer periphery of the discs 4 and extend at a predetermined angle to the tangent to the "." "* * · ···" ·····················································. ·· Ο * * * **
    Slices 4 - from the discs 4 away to the outside. The outer blades 6 have a non-symmetrical aerodynamic profile (airfoil), the two sides of the cross section are thus curved as a rule, and to different degrees. Preferably, the trailing edges 24 of the profiles are at a distance from the center of the discs 4 that is greater than or equal to 90% of the disc radius. The largest part of the profile is thus outside the discs 4, it protrudes out of these, which is clearly visible in Fig. 2. The latter also means that the majority of the surface of the discs 4 is free of any obstacles. Of course, other designs are possible.
    The blade height of the outer rotor 6 corresponds to the inner distance between the closure members 5, 13, i. the Laufschaufein 6 are limited to the disc-shaped part of the end elements 5, 13. The blade vertical axis is perpendicular to the surface of the discs 4 and parallel to the axis of rotation of the rotor 1 and the longitudinal axis of the shaft 3. In all blades 6 of this series, the blade longitudinal axis with the tangent to the discs 4 in the connection point the same angle. This angle may vary depending on the particular design. The function of this series is in addition to the increase in efficiency (additional moment by buoyancy and impulse) and the increase in strength and mechanical stability of the entire rotor assembly. The latter is ensured by the fact that the individual rotor blade 6 of the outer row of rollers have recesses 33 in which the outer edges of the disks 4 are inserted in a form-fitting manner. Thus, the individual blades 6 also have the function of peripheral spacers. In addition, the individual blades 6 of the outer race are connected to the outer discs 5 by means of the third connecting elements 22. A single outer race 6 of the outer race with recesses 33 is shown in FIG.
    This arrangement of the outer blades 6 and the disks 4 distinguishes this invention from known designs of gas and steam turbines, where the profiles or blades 6 are completely within the radius of the disks 4 and thus a negative effect on the boundary layer-related effects have the gaps 19.
    In addition to the previously described elements, the rotor 1 includes yet another row of blades - the inner race consisting of the inner blades 7. This row of races is located in the space between the inner ends of the inner guide row, consisting of the inner vanes 12, and the flow-guiding element 17th wave 3, which is a kind of "front end". the wave is 3. The function of this inner race is the utilization of the remaining energy in the flow as it leaves the disc area of the rotor 1. This series of courses should, as usual with a so-called "cantilever MM Μ • Φ *« * • · · t · * 4 «· · · Q4 Φ 4 · * 4 * * * Φ * * * 4 ·« · · · 4 4 · · 4 type turbine ", as equal pressure stage. The inner blades 7 are not designed here as a free-ending blade, but to avoid or minimize the vibrations, provided with a shroud 25 which is formed as a circular ring and the same radial dimension as the inner blades 7. Die in 1 lower ends of the blades 7 are connected to each other with a first ring 26, which in turn is connected to the shaft 3 via the same first connecting elements 15, which are used for the connection with the lower end element 13.
    The multi-part housing 2 comprises an inflow region 27, via which the fluid is introduced into the intermediate spaces 19 between the panes 4. In addition to the spaces 19 between the disks 4, the fluid flows through the two guide rows consisting of outer vanes 11 and inner vanes 12 and through the two rows of runners consisting of outer vanes 6 and inner vanes 7 where a portion of the energy, which is contained in the fluid is discharged, and thus the efficiency compared to prior art turbine models is improved.
    The multi-part housing 2 consists of a lower 8 and upper housing part 9. The two guide rows - outer vanes 11 and inner vanes 12 - are connected to the housing 2. The outer Leitschaufein 11 are connected to fourth connecting elements 28 with the lower housing part 8. The fourth connection elements 28 may be e.g. be designed as screws. The outer guide row with the guide vanes 11 is located between the inflow region 27 and the outer race with the blades 6. The preferred shape of the outer Leitschaufelri 11 is shown in FIG. 2. They have a cross-section bounded by straight lines. In this case, three lines form an obtuse-angled triangle. The base of the triangle points into the interior of the housing (towards the axis of rotation of the shaft 3). The shorter side of the triangle is tangent to the circle on which the vanes 11 are arranged and form the outer guide row.
    The simple - two-dimensional - blade shape causes an increase in the kinetic energy of the fluid with at the same time minimal losses and production costs. Of course, other shapes or cross sections of the guide vanes 11 are possible.
    The lower ends of the outer vanes 11 are connected to a second ring 29 and the second ring 29 - and thus all outer vanes 11 - is connected to the lower housing part 8 with fourth connecting elements 28. «T« Μ ··· «
    The inner guide row consists of the inner guide vanes 12 and is located - seen in the radial direction - between the inner edge of the discs 4 and the inner row of rollers consisting of the inner Laufschaufein 7. The preferred form is shown in FIG. The inner guide vanes 12 are the same in shape and orientation as the outer vanes 11. In the preferred embodiment shown here, the upper ends of the inner vanes 12 are connected to a third ring 30 and the ring 30 - and thus all inner ones Guide vanes 12 - is connected to the upper housing part 9 by means of fifth connecting elements 31. These connecting elements 31 can also be designed as screws.
    The function of the two control lines is an increase in the kinetic energy of the flow medium with the simultaneous optimization of the input direction with respect to the disks 4 and the blades 6, 7 of the outer and inner run series. The entire housing 2 forms with its spiral shape a fluid-conducting device with the Be of the optimal distribution of the mass flow and the speed over the entire circumference of the diffuser. An outer vane 11 is disposed so as to connect to the inner wall of the input passage forming the beginning of the inflow section 27.
    The lower housing part 8 includes a bearing 10 and is connected to the fourth connecting elements 28 with the outer vanes 11. In a preferred embodiment, the rotor 1 is rotatably mounted in the housing 2 of the turbine. But it can also be rotatably mounted in areas outside the housing 2 by means of corresponding (not shown) storage facilities. A fluid outlet 16 in the form of a diffuser is an integral part of the upper Gehäuseteiis 9. Both the lower 8 and the upper housing part 9 have on its inner side concentric shapes, in conjunction with the corresponding shapes on both end elements 5,13 of the rotor 1, have the function of reducing leakage losses. The upper housing part 9 is connected to the lower housing part 8 by means of sixth connecting elements 32, such as screws.
    In general, for the design of the turbine according to the invention to say that the number of outer blades 6 and their characteristics (nose radius, trailing edge radius, curvature, chord length) are selected at least depending on the radius of the discs and the desired peripheral speed. The number of inner blades 7 and their characteristics (nose radius, trailing edge radius, curvature, chord length) are approximately dependent on the mass flow of the fluid. The number of guide vanes 11,12 of the two Leitreihen and their characteristics (dimensions, ratio mouth / pitch, etc.) are dependent on the dimension of the discs 4 and the application of the turbine. The corresponding interpretations can be made by the person skilled in the art * t ♦ # * · Μ · · · · · I I ·· * and are therefore not explained here. Likewise, the number and shape of the concentric labyrinth seals as well as the diffuser characteristics of the fluid outlet 16 are variable depending on the particular design of the turbine. Depending on the design of the turbine this can be operated as a gas or steam turbine 5. The direction of the axis of rotation of the turbine is arbitrary, i. It is both a vertical arrangement and a horizontal arrangement or an oblique arrangement in space realized.
    10 REFERENCE LIST 15 20 25 30 1 runner 2 housing 3 while 4 disk 5 cover disk {upper end member) 6 outer rotor 7 inner rotor 8 lower case 9 upper case 10 bearing 11 outer stator 12 inner stator 13 lower end member 14 depressions 15 first connector 16 fluid outlet 17 flow guiding element of the shaft 3 18 spacer element 19 space between the disks 4 20 second connecting element 21 nut 22 third connecting element 23 elevations 24 trailing edge of the outer rotor blade 6 25 shroud 35 26 first ring 27 inflow region 28 fourth connecting element 29 second ring 30 third ring 31 fifth connecting element 32 sixth connecting element 33 recesses
    权利要求:
    Claims (15)
    [1]


    1. Rotor (1) for a radially flowable turbine, in particular micro gas turbine having a shaft (3) and one or more, then arranged parallel to each other, discs (4), wherein on the outer Extent of the discs outwardly directed outer blades (6) are arranged, characterized in that the discs (4) between the outer periphery and the shaft (3) have at least one recess, within which inner blades (7) are provided.
    [2]
    2. Rotor according to claim 1, characterized in that the discs to form a recess in the form of a circular ring and the inner blades (7) within the inner circumference of the discs (4) are arranged.
    [3]
    3. Rotor according to claim 1 or 2, characterized in that the inner Laufschaufein (7) at a distance from the discs (4).
    [4]
    4. Rotor according to one of claims 2 to 3, characterized in that the ratio of the outer to the inner radius of the discs (4) is between 1.1 and 3.
    [5]
    5. Rotor according to one of claims 1 to 4, characterized in that the discs (4) have flat surfaces.
    [6]
    6. Rotor according to one of claims 1 to 5, characterized in that the discs (4) - seen in the axial direction - between at least partially disc-shaped end elements {5,13) are arranged.
    [7]
    7. A rotor according to claim 6, characterized in that the end elements (5, 13) on its side facing away from the discs (4) have a plurality of concentric recesses (14).
    [8]
    8. Rotor according to one of claims 1 to 7, characterized in that the vertical axis of the outer (6) and / or the inner rotor blades (7) forms an angle with the axis of rotation of the shaft (3).
    [9]
    9. Runner according to one of claims 1 to 8, characterized in that the inner and outer blades (6, 7) over their entire height have the same cross-section.
    [10]
    10. Rotor according to one of claims 1 to 9, characterized in that the outer blades (6) are aerodynamically shaped.
    [11]
    11. Rotor according to one of claims 1 to 10, characterized in that the trailing edges of the outer blades (6) have recesses into which the outer edges of the discs (4) - in particular form-fitting - are inserted.
    [12]
    12. Radially flow-through turbine, in particular micro gas turbine, comprising a rotor (1) according to one of claims 1 to 11 and a housing (2) with a bearing (10) for the shaft (3) of the rotor (1), wherein the housing ( 2) surrounds the rotor (1) and has an inflow opening leading into an inflow region (27) and a fluid outlet (16), characterized in that the housing (2) has outer vanes (11) which are located outside the outer rotor blades (6). of the rotor (1) are arranged.
    [13]
    13. A turbine according to claim 12, characterized in that the housing (2) inner guide vanes (12) which are arranged in the radial direction between the inner rotor blades (7) of the rotor (1) and the discs (4).
    [14]
    14. Turbine according to claim 12 or 13, characterized in that the housing (2) has a plurality of concentric elevations (23) which protrude into the recesses of the end elements (5, 13) of the rotor (1).
    [15]
    15. A turbine according to any one of claims 12 to 14, characterized in that the inner and outer guide vanes (11,12) over their entire height have the same cross-section, wherein the cross-section of straight lines is limited.
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    同族专利:
    公开号 | 公开日
    AT512653B1|2013-10-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4201512A|1977-08-23|1980-05-06|Cerla N.V.|Radially staged drag turbine|
    WO2008070369A2|2006-12-05|2008-06-12|Fuller Howard J|Wind turbine for generation of electric power|FR3062156A1|2017-01-24|2018-07-27|Bernard Etcheparre|CENTRIFUGAL TURBINE WITH EDGE AND AUBES REPORTED DISCS|
    FR3062158A1|2017-01-24|2018-07-27|Bernard Etcheparre|MIXED HYBRID CENTRIFUGAL TURBINE, TCHM, WITH COMPRESSION AND THERMAL EXCHANGER FUNCTIONS|
    IT201800007430A1|2018-07-23|2020-01-23|MACHINE FOR THE GENERATION OF ENERGY BY EXPLOITING THE FLOW OF A FLUID|
    法律状态:
    2018-02-15| MM01| Lapse because of not paying annual fees|Effective date: 20170628 |
    优先权:
    申请号 | 申请日 | 专利标题
    AT7242012A|AT512653B1|2012-06-28|2012-06-28|Rotor and radially flowable turbine|AT7242012A| AT512653B1|2012-06-28|2012-06-28|Rotor and radially flowable turbine|
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