• 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:
    A flywheel (13) having a rotational body (131) related to a rotational axis and having a radially outer flywheel mass part (24) tapering in the radial direction, adjoining an inner shaft connecting part (26), hollow projecting end parts (24 ') are formed; the outer flywheel mass part (24) has on its outer side an all-round radial indentation (25).
    公开号:AT512657A4
    申请号:T50183/2012
    申请日:2012-05-15
    公开日:2013-10-15
    发明作者:Alexander Dipl Ing Dr Schulz；Thomas Dipl Ing Hinterdorfer；Harald Dipl Ing Sima；Johann Dr Wassermann；Manfred Ing Neumann
    申请人:Univ Wien Tech；
    IPC主号:
    专利说明:

    1
    The invention relates to a flywheel with a rotation body related to a rotational body having a radially outer flywheel mass part, which tapers in the radial direction, adjoins an inner shaft connecting part, wherein hollow projecting end portions are formed. Such a flywheel is known from McGroarty et al., &Quot; Flywheel Energy Storage System for Electric Start & s All-Electric Ship ", Electric Ship Technologies Symposium, 2005 IEEE, pp. 400-406, 25-27 July 2005.
    Flywheels are used in rotating machinery, especially electric motor / generators for energy storage and form the central component of a flywheel energy storage system, short FESS {Flywheel Energy Storage System). Due to its shape and mass, the rotor has a significant influence on the energy content and the energy density {energy content per mass), on the total cost of the system as well as on the power loss of the bearing. Due to outstanding material properties, composite materials (mostly carbon fiber composite materials, CFRP, or a combination of CFRP with glass fiber composites, GRP) are used for flywheels. These materials have outstanding material properties in the fiber direction, but only a low strength transverse to the fiber direction, which results in many common rotor designs a suboptimal material utilization, as very high mass forces act in the radial direction.
    In principle, a distinction can be made in the rotor designs between an inner and an outer rotor. The internal rotor is a solid shaft as a carrier for bearing and motor / generator components. The outer rotor uses a hollow shaft, and the electric machine and the bearing engage the inner radius of the hollow shaft.
    In the case of flywheels commercially available on the market, as well as flywheels made of fiber-reinforced materials and having a rectangular (axial) cross-section, as well as internal rotors with a generally rectangular flywheel cross-section made entirely of steel, as mentioned above. Another known rotor design is an internal rotor with H-shaped cross-section 2 and composite flywheel.
    Current research projects usually deal with rotors made of fiber composite materials (carbon fibers, glass fibers). Represented here are in turn internal rotor with rectangular cross-section (Herbst et al., "Design, Fabrication and Testing of 10MJ Composite Flywheel Energy Storage Rotors, SAE Technical Paper 981282, 1998, Jansen et al., &Quot; G2 Flywheel Module Design " (NASA / CR-2006-213862) or H-section (Park et al., "Development of 5kWh flywheel energy storage system using MATLAB / xPC Target", World Congress on Computer Science and Information Engineering 2008 IEEE, ( McGroarty et al., Flywheel Energy Storage System for Electric Start and All-Electric Ship, Electric Ship Technologies Symposium, 2005 IEEE, S 400-406, July 25-27, 2005.
    A completely different structure is the external rotor. Instead of a shaft this has a central stator unit, which is enclosed by the flywheel. The most common cross-sectional shape for this rotor design is rectangular (eg, Be-no et al., "End-of-life design for composite rotors", IEEE Transactions on Magnetics, 37 (1) (2001): 284-289) or H- shaped.
    In this design, in a version with magnetic bearings, the general problem that increases the air gap of the magnetic bearing and the motor / generator due to the occurring elongation of the rotor speed-dependent. In order to ensure a sufficient air gap even at a minimum speed, thus resulting in a maximum speed, a much larger air gap, which leads to a reduction in energy efficiency due to the greater required flooding or to a reduction in power. Another major problem is the almost direct contact of the motor / generator with the composite material. The heat loss of the soft magnetic motor / generator rotor can be given off due to the vacuum anyway only by radiation; Furthermore, composites can only be exposed to a low temperature load. Furthermore, the support structure is a major design challenge. Due to the comparatively large inner radius, very high stresses occur in the metal. 3
    The theoretically ideal design of a flywheel rotor, if only the functionality of the flywheel without consideration of the motor / generator and bearing functionality is considered, represents a thin-walled hollow cylinder made of composite material as external rotor, on the inside in the upper and lower part of the storage and in the middle of the motor / generator are arranged. This is because with a thin-walled hollow cylinder only small radial stresses can form and thus the greatest stresses occur in the circumferential direction and thus in the fiber direction (compare Arnold et al., "Deformation and Life Analysis of Composite Flywheel Disk System", Composites: Part B 33 (2002): 433-459).
    Due to the above-mentioned problems, the typical rotor shape of modern flywheel designs is usually an internal rotor consisting of a metal shaft for mounting the bearing and motor / generator assemblies and a cylinder or H-shaped composite flywheel. connected to the shaft by an annular connecting part.
    In the case of an axial-H-shaped rotor, a large part of the mass is arranged far outward for the largest possible moment of inertia. The occurring natural frequencies limit this connection with a very small axial length based on the length of the cylindrical flywheel part. The most heavily loaded areas are located at the height of the connection, since the largest mass forces occur here. High voltages occur at the transition from the connecting part to the hollow cylinder due to the bending stress state. The outer areas of the H-shape, where the largest proportionate moments of inertia can be achieved, are only slightly loaded. A direct consequence of this is that the strength properties of the composite material can only be used insufficiently in geometries of the flywheel mass that can be produced using conventional production methods. This results in higher material costs and due to the heavier flywheel a larger required bearing dimensioning; As a result, higher costs and a reduction in the energy efficiency of storage result. 4
    It is now an object of the invention to propose an embodiment of a flywheel as stated above, in which the highest possible energy density, depending on the material and dimensions, can be achieved, and in which a good material utilization or use of the strength properties of the material is made possible.
    The flywheel according to the invention of the type mentioned is characterized in that the outer flywheel mass portion has on its outer side a radially extending recess extending all around. This radial indentation leads, as explained below, to a considerable increase in the energy density both in internal rotor and in external rotor designs.
    Advantageous embodiments and further developments are specified in the dependent claims.
    So it can, e.g. for manufacturing reasons, be favorable if the outer flywheel mass part in the axial connection to the recess has a generally hollow cylindrical shape.
    On the other hand, it is advantageous for additional energy density optimization if the outer flywheel mass part, viewed in axial section, has legs that extend generally obliquely away from the center of the recess to opposite sides. In this case, one or both of the projecting end portions may extend parallel to the axis and thus define a hollow cylinder. For good space utilization in the machine {motor / generator), the shaft connecting part can also have a smaller axial extent than the outer flywheel mass part.
    Above all, the outer contour of the flywheel, in addition to or alternatively, but also the inner contour, is expedient with a "soft". or steady course. It is advantageous if the flywheel mass part outside and / or inside has a contour with one or more straight segments. Furthermore, it is favorable if the flywheel mass part outside and / or inside has a contour with one or more curve segments. Preferably, at least one arcuate segment is present here. But it is also possible to have at least one
    5 of a higher order curve, e.g. Ellipse or polynomial, running segment provided. For ease of manufacture, it is also advantageous if the flywheel mass part outside and / or inside has a step-shaped contour. It is also expedient if the flywheel mass is constructed with joined separate rings.
    To eliminate any imbalances, it is also advantageous if the flywheel mass part · has at least one ring with receptacles, holes or the like. For attaching balancing weights.
    The flywheel body can be symmetrical or, with appropriate design of the associated system components (electric machine, storage), advantageously also asymmetric with respect to its center plane (namely, the plane with the smallest outer radius) may be formed. Preference is given to an embodiment of a fiber composite material, in particular CFRP or a combination of CFRP and GRP,
    The invention thus provides an advantageous constructive solution for, with regard to material utilization, optimum shaping of flywheels, as used for example in FESS, is.
    The core of the invention is that - contrary to a technically obvious interpretation with the highest possible mass at a large radius - a recess, d, h. Rejuvenation, the outer contour is provided in the direction of connection to the shaft.
    As mentioned, the outer contour is ideally called "softer". or continuous course, and consists for example of circular segments and straight line pieces. For functional {transport security, etc.) and / or manufacturing reasons also non-continuous courses or curves of higher order (ellipses, polynomials, etc.) are advantageous. In addition, the rotor does not have to be symmetrical with respect to its midplane. The flywheel can also be constructed as mentioned stepwise, the rings can be made separately and then joined. 6
    By tapering the outer contour in the direction of the connection to the shaft, the mass forces in the area of the shaft connection are reduced, as a result of which the radial stresses decrease. The stress in the region of the center plane shifts to the circumferential direction, in which the material strength is much higher. The strength properties of the material are thus better utilized.
    Of importance is that, by the tapering of the outer contour in the direction of connection to the shaft, "missing". Although mass leads to a reduction of the moment of inertia, but that higher speeds can be achieved due to lower radial stresses. However, since the effect of increasing the rotational speed is more important than the effect of reducing the moment of inertia, the energy content can be increased for the same mass. The non-cylindrical design of the outer contour therefore leads to better material utilization and a concomitant increase in the energy density.
    The invention will be explained below with reference to the drawing and with reference to embodiments of the prior art on the one hand and to preferred, advantageous embodiments of the invention on the other. Show it:
    Fig. 1A is a plan view of a conventional internal rotor rotor;
    1B schematically shows a quadrant of an inner rotor with a radially symmetric finite element simulation of the rotor, wherein lines with the same load are illustrated according to the puck failure criterion at maximum angular velocity (see Puck A., "Strength Analysis of Fiber Matrix Laminates") ;, Models for the practice, Carl Hanser Verlag Munich Vienna (1996));
    Fig. 2 is a graph of radial and hoop stress in the composite material in the inner rotor of Fig. 1B; Figures 3A and 3B are similar to Figures 1A and 1B, but now for an internal rotor with H-shaped cross-section 7 according to the prior art;
    Fig. 4 shows a structure of a conventional external rotor with H-shaped cross section;
    5 shows a representation of a basic structure of a FESS arrangement with an inner rotor rotor and with a flywheel according to a preferred embodiment of the invention;
    6 shows a rotor as provided in the arrangement according to FIG. 5 in a three-dimensional representation, partially cut away;
    7 shows a diagram of a quadrant of a rotor with projecting paraxial end parts, with a representation of the lines of the same load according to the puck failure criterion corresponding to the illustrations in FIGS. 1B and 3B;
    Fig. 8 is a comparable illustration of a flywheel quadrant as in Fig. 7, but now with an outwardly diverging end portion or leg;
    FIG. 9 shows schematically in a common diagram a comparison of the energy content and the energy density of the known embodiments according to FIGS. 1B and 3B on the one hand and the embodiments according to FIGS. 7 and 8 on the other hand; Figures 10 to 14 in, Figures 7 and 8 comparable representations of further embodiments to show different possible contours of the flywheel; Figures 15 and 16 are comparable views of cantilevered end portions of the flywheels, with rings for receiving balancing weights; and
    Fig. 17 in a representation similar to that in Fig. 10 to 14, an embodiment as an external rotor.
    Figures 1A to 4 relate to rotor or flywheel designs according to the prior art. 8th
    Figures 1A and 1B show a disk-shaped rotor 1 with a shaft 2, e.g. made of aluminum, and with a disk 3, e.g. CFK, as flywheel.
    The most important material data of the CFRPs (epoxy resin reinforced HTS40 carbon fibers from TohoTenax) and aluminum used for this and the other rotors listed are given in the following Table 1.
    CFC modulus of CFRP transverse to fiber direction 9 GPa Density of CFRP 1535 kg / m3 CFRP tensile strength in fiber direction 2179 MPa CFRP tensile strength transverse to fiber direction 98 MPa Modulus of elasticity aluminum 70 GPa density aluminum 2700 kg / m3 tensile strength aluminum 275 MPa
    Fig. 1B shows an axisymmetric finite element simulation of the rotor 1, wherein the symmetry of the rotor 1 was used with respect to its center plane 4. Shown are lines with the same load according to the puck failure criterion at maximum angular velocity. This criterion is normalized, i. at a value of 1, failure occurs. Since the rotor 1 was dimensioned with a safety of 2, the maximum value is 0.5.
    By way of example, the rotor in FIG. 1B was designed for an energy content of 5 kWh and achieves this at a maximum angular velocity of 2010 rad / s. The rotor mass is 260 kg and the moment of inertia around the axis of rotation is 9.89 kgm2. From these data results an energy density of 19.23 Wh / kg. (For efficient operation of the electric machine, a FESS is operated within a certain speed range, therefore, the energy content does not correspond to the kinetic energy, and the minimum operating speed is chosen here and then one third of the maximum speed.) 9
    The highest load occurs at an average radius of about 0.22 m and is approximately constant in the axial direction, apart from edge effects, as can be seen in FIG. 1B. This highest load is due to the relatively low maximum tensile strength transverse to the fiber direction of composites. The mass forces occurring at the connection point to the shaft 2 lead to high radial stresses and therefore to poor material utilization.
    Fig. 2 shows the gradients of radial and hoop stress in the composite (flywheel 3) and is intended to illustrate this fact. The radial stress 5 has at its maximum a safety factor of 2 to the maximum permissible value from Tab. 1, while the safety of the peripheral voltage 6 shown by dashed lines is much higher. The excellent properties of the composite in the fiber direction are therefore not sufficiently utilized.
    The rotor types mentioned below are designed for better comparability with the same mass as the rotor according to FIG. 1B.
    A more expedient rotor geometry is shown in FIGS. 3A and 3B (also prior art): With the same mass, an H-shaped structure results in a higher moment of inertia (13.18 kg.sup.2); As a result, a higher energy content of 5.7 kWh and thus a higher energy density of 22.19 Wh / kg are achieved. As with the structure in Fig. 1B, very high radial stresses occur at a radius of about 0.22 m. Furthermore, due to the cantilevered H-shape and its widening, high bending stresses occur at the transition, which limit the maximum achievable angular velocity (1871 rad / s).
    Fig. 4 shows in a schematic view similar to Fig. 1A, a different type of rotor, an external rotor 1 ', with a hollow shaft 2' and with an external flywheel 3 ', wherein the most common cross-sectional shape for this rotor design is rectangular.
    Inside there is a central stator unit which is not illustrated in more detail and which is enclosed by the rotor or flywheel 10. The hollow shaft 2 'and the actual flywheel 3' are connected to one another via a connecting part 7 'which is H-shaped in cross-section; see. Incidentally, also the connection part 7 according to FIG. 3A.
    In Fig. 5 and 6, an example of a flywheel energy storage system, short FESS, 10 is shown, wherein an inner rotor rotor 11 is inserted, which has a shaft 12 with a rotation axis X-X. The electric machine (motor / generator) is designated 32 and has an outer stator with an upper support sleeve 14 and a lower support sleeve 15 for the usual and not all closer-recorded electromagnets, e.g. 16 for radial storage, on. Furthermore, an upper axial magnetic bearing 17 and a lower axial magnetic bearing 18 are illustrated for the shaft 12 of the rotor 11, as well as catch bearings 19 and 20. Radial position sensors 21 and an axial position sensor 22 are used to detect the position of the shaft 12 relative to the upper or Lower carrier sleeve 14 and 15, which is required for the storage control. Finally, a housing 23 for the FESS 10 is also shown schematically.
    The on the shaft 12, i. On the rotor 11, attached components of the magnetic bearing system are conventional and in Fig. 5, although schematically illustrated, but not specified, and it may also be unnecessary for a detailed explanation of these components.
    The shaft 12 is preferably designed as a solid shaft to serve as a support structure for the required bearing and motor / generator components and as a bearing surface for the fishing camps 19, 20.
    The flywheel 13 or its rotational body 13 '(FIG. 6) with its radially outer flywheel mass part 24 consists of a composite material.
    The rotor 11 runs within the housing 23, which is vacuum-tight and evacuated, and which also serves as a carrier of the stator components (see the carrier sleeves 14, 15) about the axis X-X. As mentioned, the stator laminations of the 11th to the carrier sleeves 14, 15
    Storage and the electrical machine, windings and the sensors 21 and 22 attached.
    FIG. 6 shows the rotor 11 of the FESS arrangement 10 according to FIG. 5 in a cutaway three-dimensional representation. The flywheel mass portion 24 is, as is particularly clear here, in addition to the axial section shown in FIG. 5, can be seen with a taper or indentation 25 on the outer contour, so that, for example, a spool-like appearance of the flywheel or the flywheel 13 results, in particular from Fig. 6 can be seen.
    To manufacture such a rotor 11 with flywheel 13, a winding method known per se is suitable, in which the fibers (carbon fibers, glass fibers) are passed through an impregnating bath and then deposited wet on a rotating core.
    From the viewpoint of the strength of the rotor 11, a fiber angle of 90 ° to the rotation axis X-X is ideal. Alternatively, preimpregnated fibers - so-called prepregs - can be used.
    It can further be seen from FIG. 5 that the rotor 11 does not necessarily have to be designed symmetrically with respect to its center plane Y-Y (at right angles to the rotor axis X-X), even though this will often be preferable. Such asymmetric design may be useful if special space requirements with regard to the accommodation of the individual motor / generator components, etc. are to be considered.
    By the described and illustrated taper or indentation 25 of the flywheel, which runs all the way around in the circumferential direction, a substantial improvement in the material utilization can be achieved.
    In FIG. 7, in a representation similar to FIG. 1B and FIG. 3B, a quadrant of the flywheel 13 is illustrated schematically in axial section. As can be seen, the rotor geometry consists of circle segments Kn and straight lines Gn (with n = 1, 2,...) And has a tapering 25 of the outer contour. Due to the smaller outer radius r in the area of the center plane Y-Y, the moment of inertia drops to 10.93 kgmz. Due to the lower mass forces in this area, however, the radial stresses also decrease, which means higher angular velocities (2188 rad / s) are possible. Thus, the rotor 11 has an energy content of 6.55 kWh, and with a mass of 260 kg also results in an energy density of 24.58 Wh / kg. However, it would be desirable (see the drawn "load lines") to make the hollow cylindrical areas defined by the cantilevered paraxial end portions 24 'more efficient, i.e., more efficient. to burden more heavily.
    By tilting the cantilevered parts 24 ', as shown in Fig. 8, the benefits of the invention can be further exploited. Due to the inclination, the bending stresses at the transition from the inner connection part 26 to the (actual) flywheel part 24 are "defused". Thus, the radial stresses decrease, and the circumferential stresses increase, resulting in a more favorable stress state and material utilization due to the material orientation. At approximately the same angular velocity as in the rotor 11 according to FIG. 7 (2151 rad / s), the moment of inertia in the rotor 11 according to FIG. 8 is 14.9 kgm2, which corresponds to an energy content of 8.27 kWh. The same mass results in an energy density of 31.18 Wh / kg, which is a significant increase compared to the other structures.
    This can be seen in particular from the schematic representation of FIG. 9, in which the four previously mentioned rotor structures, according to FIGS. 1B, 3B, 7 and 8, are juxtaposed, and in which energy content 30 and energy density 31 are illustrated. It can be seen that in the embodiments according to the invention, that is to say according to FIGS. 7 and 8, in this exemplary embodiment, an increase e.g. the energy density 31 of 65% can be achieved.
    In the embodiments shown so far, the rotor contour is always composed of straight segments Gn and circle segments Kn. For functional reasons {transport security, etc.) and / or production-technical reasons, however, non-continuous courses or curves of higher order, such as, for example, can also be used. Ellipses, polynomials, etc., be beneficial; see. For example, the embodiments of Figures 10 to 12 and 14. Referring to FIG. 13 is the
    13
    Flywheel part 24 stepped, for example, from individually wound composite rings 24A-24E constructed. These rings 24A-24E can be manufactured separately and then joined. This results in a stepped contour, as shown in Fig13. In general, with a step-shaped training, whether in one piece or with separate rings, a simpler production possible because the fibers can not slip off the winding core during winding.
    As a significant advantage, which is given in the embodiments according to Fig.7, 8 and 10 to 14, it should be mentioned in any case that the taper 25 of the outer contour leads to a, in the sense of material orientation, better stress state. The radial stresses are reduced and thus the hoop stresses are increased.
    The rotor structures of Figs. 8 and 10 to 14 still have the additional advantage that the " slope " the inner contour to an even better stress distribution at the transition to the inner "disc " and thus leads to lower bending stresses. In addition, it can be used to increase the radius of gyration, whereby a higher energy content is achieved with the same mass.
    The thickness of the "cantilevered" Part 24 '{Figures 7, 8 and 10 to 14) is sufficiently large to choose to achieve high stiffness and thus high elastic natural frequencies. The contour of the rotor 11 should be chosen so that the energy density becomes maximum. There are manufacturing limits. Starting from the loading state of the H-shaped flywheel, which can be produced with simple production-technical means, as shown in FIG. 3B, it is already clear in terms of geometry optimization that it makes sense to use the flywheel part designed as a hollow cylinder as a double hollow cone or in a hollow cone-like shape to execute {see Fig. 8, etc.). This leads to an increase in the radius of gyration and to a reduction of the bending stresses at the transition from the inner disk 26 to the outer flywheel mass part 13.
    The strong anisotropy due to the lamellar molecular structure of carbon fibers results in a low strength of the
    14 bundwerkstoffs transverse to the fiber direction, whereby only low radial stresses are allowed. The due to the inertial forces at the required maximum speeds very high radial stresses can be reduced by smaller wall thicknesses. As a result, a more favorable stress state is achieved, since the circumferential stresses increase and the strength in this direction is substantially higher. However, lower wall thicknesses also lead to lower natural frequencies. In flywheel applications with low engine power, an operation below elastic natural frequencies is sought, as a driving through the rotor natural frequencies - due to the time required for this - is critical. A fiber angle other than 90 ° can provide additional stiffness in the direction of the X-X axis. Here is a compromise of strength and dynamic requirements to find.
    Due to the stated advantages, the invention allows better material utilization, an increase in the energy density and thus lower material costs compared to conventional rotor structures.
    Due to the significantly better material utilization, towards a "Fully-Stressed-Design", on the one hand the investment costs can be reduced considerably due to the higher energy density and on the other hand the total energy efficiency can be increased, which makes highly efficient flywheels economically viable for a wide range of applications. The basic objective function is to minimize mass for a given energy content and maximize energy efficiency. Ideally, this results in a geometry in which each area is maximally loaded according to a suitable failure criterion, from which the best possible material utilization follows.
    The above-mentioned composite material (CFRP or CFK-GFK combinations) has a strong anisotropy, but also excellent material properties in the fiber direction. Bare glass fiber composites (GRP) are less anisotropic and also less expensive. However, their stiffness characteristics and especially their density are less ideal for flywheel applications compared to CFRP. 15
    A "concentricity" of the rotor, i. the balancing quality, has an important influence on the bearing forces of the rotor or on the required air gap in the magnetic bearing of the rotor and thus on the energy efficiency of the entire system, and this is particularly true for the present flywheels with the high speeds addressed * A Positioning of balance weights in areas with high radial stresses is unfavorable in terms of strength. This complicates the assembly, since it is necessary to avoid notches or a weakening of the material. In addition, it should be ensured that the attached balancing weights remain in place throughout the entire life cycle.
    In order to solve this problem, the present flywheel 13 can incorporate special rings 27 (see, e.g., Figures 12, 14) for receiving balance weights in the composite flywheel 13, which provide balance weights 28 such as balancing weights. Holes (see Fig. 12) have. At the required location these are partially or completely filled with material. Alternatively, a material removal 29 (see Fig. 14) from the ring 27 is possible to compensate for an imbalance. The placement of balancing weights is optimally integrated into the rotor structure, taking into account manufacturing limits.
    Fig. 15 shows a simulation of an exemplary rotor 11 with an inside mounted balance ring 27 made of epoxy resin. The lines with the same failure criterion remain approximately unchanged, i. that the ring 27 can be advantageously integrated at this point.
    The ring 27 may have various embodiments (see Figures 12, 15 and 16) and may also be mounted after the manufacture of the rotor (e.g., Figures 12 and 14).
    Although the invention has been explained above with reference to preferred exemplary embodiments, further modifications and modifications are possible within the scope of the claims. In particular, it is also conceivable to provide the present flywheel in conjunction with an external rotor 11J (see Fig. 17 in connection 16 with Fig. 4), whereby it would even be conceivable to use the actual flywheel, i. to integrate the flywheel mass portion 24, with the hollow shaft 12 to which the required components of the electrical machine and the bearing are mounted, to form a unitary composite component. Furthermore, other materials than CFRP and GFRP, such as Polyethylene fibers etc. possible.
    权利要求:
    Claims (15)
    [1]
    17 claims: 1. flywheel (13) with a rotation axis (XX) related to a rotational body having a radially outer flywheel mass portion (24), which tapers in the radial direction, to an inner shaft connecting part (26), wherein hollow cantilevered end portions (24 ') are formed, characterized in that the outer flywheel mass portion (24) on its outer side has an all-round extending radial recess (25).
    [2]
    Second flywheel according to claim 1, characterized in that the outer flywheel mass portion (24), viewed in axial section, from the center of the recess (25) away on opposite sides generally obliquely outwardly extending legs.
    [3]
    3. flywheel according to claim 1 or 2, characterized in that at least a portion of the projecting end portions (24 ', 24 ") is parallel to the axis and so defines a hollow cylinder.
    [4]
    4. flywheel according to claim 1, characterized in that the outer flywheel mass portion (24) in the axial connection to the recess (25) has a generally hollow cylindrical shape (Fig.7).
    [5]
    5. flywheel according to one of claims 1 to 4, characterized in that the shaft connecting part (26) has a smaller axial extent than the outer flywheel mass portion (24).
    [6]
    6. Flywheel according to one of claims 1 to 5, characterized in that the flywheel mass portion (24) has outside and / or inside a contour with one or more straight segments (G).
    [7]
    7. flywheel according to one of claims 1 to 6, characterized in that the flywheel mass portion (24) on the outside and / or inside a contour with one or more curve segments (K).
    [8]
    8. flywheel according to claim 7, characterized by at least 18 a circular arc-shaped segment.
    [9]
    A flywheel according to claim 7 or 8, characterized by at least one corresponding to a higher order curve, e.g. Ellipse or polynomial, running segment.
    [10]
    10. flywheel according to one of claims 1 to 6, characterized in that the flywheel mass portion (24) on the outside and / or inside has a stepped contour (Fig.13).
    [11]
    11. Flywheel according to claim 10, characterized in that the flywheel mass part (24) is constructed with joined separate rings (24A-24E).
    [12]
    12. flywheel according to one of claims 1 to 11, characterized in that the flywheel mass portion (24) has at least one ring (27) with receptacles, holes or the like. For attachment of balancing weights.
    [13]
    13. Flywheel according to one of claims 1 to 12, characterized in that the flywheel body (24) is formed asymmetrically in the axial direction (Figure 5).
    [14]
    14. Flywheel according to one of claims 1 to 13, characterized by an embodiment of a fiber composite material.
    [15]
    15. Flywheel according to claim 14, characterized in that the composite material is a CFRP material.
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    同族专利:
    公开号 | 公开日
    WO2013170284A1|2013-11-21|
    AT512657B1|2013-10-15|
    EP2850339A1|2015-03-25|
    US20150128757A1|2015-05-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5628232A|1994-01-14|1997-05-13|Rosen Motors Lp|Flywheel rotor with conical hub and methods of manufacture therefor|
    DE19651668A1|1996-12-12|1998-07-23|Wtz Motoren & Maschforsch Gmbh|Flywheel for high rotational speeds|
    US20100206126A1|2008-07-28|2010-08-19|Ward Spears|Advanced Flywheel Hub and Method|
    US20100231075A1|2008-10-31|2010-09-16|Young Hee Han|Large capacity hollow-type flywheel energy storage device|
    DE613427C|1935-05-18|Siemens Schuckertwerke Akt Ges|flywheel|
    DE159250C|
    GB1559314A|1975-09-04|1980-01-16|Honda Motor Co Ltd|Flywheel|
    US5566588A|1994-01-14|1996-10-22|Rosen Motors Lp|Flywheel rotor with conical hub and methods of manufacture therefor|
    JP4655421B2|2001-07-03|2011-03-23|いすゞ自動車株式会社|How to install the flywheel|US9267570B2|2008-07-28|2016-02-23|Beacon Power, Llc|Advanced flywheel hub and method|
    EP2698557B1|2012-08-14|2014-10-29|Enrichment Technology Company Ltd.|Flywheel energy storage device|
    法律状态:
    2018-01-15| MM01| Lapse because of not paying annual fees|Effective date: 20170515 |
    优先权:
    申请号 | 申请日 | 专利标题
    ATA50183/2012A|AT512657B1|2012-05-15|2012-05-15|flywheel|ATA50183/2012A| AT512657B1|2012-05-15|2012-05-15|flywheel|
    EP13728929.4A| EP2850339A1|2012-05-15|2013-05-13|Flywheel|
    PCT/AT2013/050106| WO2013170284A1|2012-05-15|2013-05-13|Flywheel|
    US14/401,420| US20150128757A1|2012-05-15|2013-05-13|Flywheel|
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