FLYWHEEL ENERGY STORAGE SYSTEM

Abstract

Flywheel system properties are enhanced with rim designs that control stress at operational rotational velocities. The tensile strength of fiber-resin composites can be aligned with radial forces to improve radial stress loading. Loops with composite casings can be arranged around the flywheel circumference with a majority of the fibers being aligned in the radial direction. The loops can enclose masses that contribute to energy storage in the flywheel system. Masses can be arranged around the hub circumference with a hoop wound composite casing enclosing the masses and hub. The masses subjected to radial forces are radially displaced with increasing rotational velocity and can provide compressive force to the fiber-resin composite to contribute to maintaining composite integrity. With the alignment of fibers in hoop or radial directions, higher loading permits increase rotational velocities, which can significantly add to the amount of energy stored or produced with the flywheel.

Claims

1. A flywheel for a flywheel energy storage system, comprising: a hub configured to rotate about a longitudinal axis; a member connected to the hub for housing a mass; and a mass being housed in the member and being configured to permit the mass to radially displace within the member.

2. The flywheel of claim 1, wherein the mass is symmetrically arranged around the hub.

3. The flywheel of claim 1, wherein the mass is radially displaced when a radial force is applied to the mass; and wherein the radially displaced mass applies compressive force to the member.

4. The flywheel of claim 1, wherein the member is arranged as one or more loops composed of fiber-resin composite material.

5. The flywheel of claim 4, wherein the hub includes a first end and a second end opposite to the first end, and wherein at least one loop is disposed on the first end and at least one loop is disposed on the second end of the hub.

6. The flywheel of claim 4, wherein at least some of the fibers in the composite material are arranged according to one or more of at least 5% aligned in the radial direction, or at least 5% aligned in the hoop direction, or in contact with the mass, or wherein the composite material is radial or hoop wound.

7. The flywheel of claim 1, wherein the flywheel is configured to have a parameter range.

8. The flywheel of claim 7, wherein the parameter range is one or more of about 15,000 rpm to about 50,000 rpm for rotational velocity or about 15.24 cm to about 203 cm for rim diameter, or about 0.5 MJ to about 3000 MJ for kinetic energy.

9. A method for constructing a flywheel for a flywheel energy storage system, comprising: coupling a member to a hub configured to rotate about the hub's longitudinal axis; disposing a mass in the member; and configurating the mass to permit the mass to radially displace within the member.

10. The method of claim 9, further comprising arranging the mass symmetrically around the hub.

11. The method of claim 9, further comprising arranging the member as one or more loops composed of fiber-resin composite material.

12. The method of claim 11, wherein at least some of the fibers in the composite material are arranged according to one or more of at least 5% aligned in the radial direction, or at least 5% aligned in the hoop direction, or in contact with the mass, or wherein the composite material is radial or hoop wound.

13. The method of claim 9, further comprising configuring the flywheel to have a parameter range.

14. The flywheel of claim 13, wherein the parameter range is one or more of about 15,000 rpm to about 50,000 rpm for rotational velocity or about 15.24 cm to about 203 cm for rim diameter, or about 0.5 MJ to about 3000 MJ for kinetic energy.

15. A method for operating a flywheel comprising: rotating the flywheel; and radially displacing an internal mass(es).

16. The method of claim 15, further comprising arranging the mass symmetrically around a hub.

17. The method of claim 15, further comprising: disposing the mass in a member, and arranging the member as one or more loops composed of fiber-resin composite material.

18. The method of claim 17, wherein at least some of the fibers in the composite material are arranged according to one or more of at least 5% aligned in the radial direction, or at least 5% aligned in the hoop direction, or in contact with the mass, or wherein the composite material is radial or hoop wound.

19. The method of claim 15, further comprising configuring the flywheel to have a parameter range.

20. The flywheel of claim 19, wherein the parameter range is one or more of about 15,000 rpm to about 50,000 rpm for rotational velocity or about 15.24 cm to about 203 cm for rim diameter, or about 0.5 MJ to about 3000 MJ for kinetic energy.

Description

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

[0022] The disclosure is described in greater detail below, with reference to the accompanying drawings, in which:

[0023] FIG. 1 is a partially cut away top view of a flywheel system;

[0024] FIG. 2 is a cross-sectional side view of an example flywheel design;

[0025] FIG. 3 is an isometric view of a flywheel hub from the example of FIG. 2;

[0026] FIG. 4 is a cut away isometric view of a portion of an example flywheel design showing attachment features;

[0027] FIG. 5 is a partial cross-sectional side view of several lobes of a 10 loop flywheel design;

[0028] FIG. 6 is a partial cross-sectional side view of a flywheel rim with rim perimeter composite loops and mass layers;

[0029] FIG. 7 is a partial cross-sectional side view of several lobes of a 12 loop flywheel design;

[0030] FIG. 8 is a partial cross-sectional side view of several lobes of a 12 loop flywheel design;

[0031] FIG. 9 is an isometric view of a 10 lobe rim design with a hub band;

[0032] FIG. 10 is an isometric view of an 8 lobe flywheel design with a perimeter hoop wound composite laminate;

[0033] FIG. 11 is an isometric view of an 8 lobe flywheel design with four quarter sections and hub end bands;

[0034] FIG. 12a is a cross sectional view of 8 radial displacing masses evenly distributed around the hub perimeter of a flywheel rim at rest;

[0035] FIG. 12b is a cross sectional view of 8 radial displacing masses evenly distributed around the hub perimeter with the masses displaced at rim designed angular velocity;

[0036] FIG. 13a is a cross sectional view of a rotating dipole with 2 radial displacing masses while at rest; and

[0037] FIG. 13b is a cross sectional view of a rotating dipole with 2 radial displacing masses with the masses displaced at designed angular velocity.

DETAILED DESCRIPTION

[0038] New flywheel rim designs are presented and discussed herein. The rims may be operated in an inclusive range of from about 15,000 rpm to about 50,000 rpm, currently limited by material strength. The rim diameter may be in an inclusive range of from about 15.24 cm (6 in) to about 203 cm (80 in), currently limited by material strength. The flywheel configurations may be able to obtain a kinetic energy an inclusive range of from about 0.5 MJ to about 3000 MJ limited by material strength.

[0039] FIG. 1 is a partially cut away side view of a current state of the art flywheel energy system 100. System 100 includes a casing 116 that houses the flywheel within a vacuum chamber 102. The flywheel has a carbon and glass fiber/epoxy composite rim 110 that is supported by radial bearings 104, 114. A hub 106 is supported with a magnetic lift system 112, which contributes to reducing parasitic losses in system 100 during operation. System 100 includes motor/generator 108 for driving the flywheel and generating electrical power from the flywheel during operation.

[0040] Current commercial fabrication techniques for rim 110 utilize a unidirectional filament winding manufacturing process, which creates a laminate with carbon fibers or carbon fibers/glass fibers oriented in the hoop or circumferential direction. The tensile strength of the carbon fibers is about 4900 MPa (711 ksi). The fiber orientation in the circumferential direction means that the carbon and/or glass fiber/epoxy laminate reacts the radial force through thickness as an out-of-plane load or stated another way, a normal/transverse load to the laminate. During operation, the radial force is observed as a load through the laminate thickness. The epoxy resin and transverse strength of the unidirectional carbon fiber filaments reacts the radial force during operation. Epoxy neat resin tensile strength is approximately half of the fiber tensile strength, or about 2758 MPa (400 ksi). In actual practice neat resin tensile strength properties are typically greater than inter-lamina resin tensile strengths. Since inter-lamina tensile properties can vary depending upon the resin, volume fraction, fabric type/material, fiber sizing and manufacturing (curing/post curing) method, the actual properties of the composite are empirically determined with coupon testing. The failure mode of rims constructed with this technique is often rim delamination due to through thickness radial stress. The radial loading on such rim designs is reacted via the lower strength laminate direction. The practical consequence of the failure mode and construction technique is a significant reduction and upper limit in rotational velocity. Although such composite construction techniques can be modified to bolster inter-laminar strength, the design is still limited with regard to flywheel rotational velocities. In addition, these rim designs obtain a high radial growth during operation, which creates a mismatch between the composite rim and metallic hub on which the rim is mounted.

[0041] Referring to FIGS. 2, 3 and 4, an example flywheel 200 is illustrated. FIG. 2 is a cross-sectional side view of a flywheel 200 according to an example design of the present disclosure. FIG. 3 is an isometric view of a flywheel sprocket or hub 208. FIG. 4 is a cut away isometric side view of a portion of flywheel 200 showing attachment features.

[0042] Flywheel 200 includes twelve lobes 202 that have a wedge-shaped cross section as depicted in FIG. 2. Each of lobes 202 extend the length of flywheel 200, and include an outer casing 212 that is composed of composite materials such as carbon fibers and/or glass fibers in a resin matrix, such as epoxy.

[0043] The fibers are, for example, wound around a hoop direction for each lobe 202 to form casing 212. For example, the fibers are aligned in a circumferential direction with respect to an individual lobe 202 in layers to form a composite laminate. The orientation of fibers can vary between the different lobes 202, e.g. between about 0 and 45 degrees with respect to a normal to a longitudinal axis of lobe 202. Each lobe 202 includes a filler material 204, which radially displaces with increasing angular velocity.

[0044] Filler material 204 may be implemented as a variable density filler. For example, filler material 204 may have a density gradient that increases with radial distance from a center of flywheel 200. Material 204 may have different density material stacked inside each lobe 202. Each lobe 202 may house and retain material 204 against radial loading during operation.

[0045] A retaining structure 206 is located internally to each lobe 202. Structure 206 may be metallic, and may be constructed to be a bolt flange that can accept, house or fix fasteners for attaching lobe 202 to hub 208. Lobes 202 can be assembled to or disassembled from hub 208 using a fastener arrangement in conjunction with structure 206. The example flywheel 200 shown in FIG. 2 has bolts 210 that are located in and pass through openings 304, as shown in FIG. 3, in hub 208 and thread into structure 206 to fasten and secure lobes 202 to hub 208. In such an example, structure 206 provides a threaded opening to receive bolts 210. Other example attachment arrangements include bolts 402 (FIG. 4) that pass through openings 304 and are threaded into nuts (not shown) that are retained in structure 206. The bolts/nuts may, in some examples, be retained inside hub 208 or in structure 206, for example by welds or recesses size and shaped to receive the bolt heads/nuts. Structure 206 may be configured to receive shear pins or shear webs (not shown) that fasten lobes 202 to rods (not shown) that extend through openings 304 from hub 208 into structure 206.

[0046] FIG. 3 shows hub 208 with curved recesses 302 that are shaped and sized to be complementary with a smaller dimension end of wedge-shaped lobes 202. Lobes 202 are snugly received in recesses 302 to permit lobes 202 to be tightly secured to hub 208.

[0047] In practice, hub 208 is mounted to an axle or rotor supported by radial bearings, such as is illustrated in flywheel system 100 in FIG. 1. Hub 208 may be suspended by a magnetic lift system 112.

[0048] The flywheel designs discussed herein seek to improve energy storage either by increasing rim angular velocity or if angular velocity is restricted by increasing mass and rim diameter, improve reliability and usability and obtain advantages that are unavailable with prior designs. The design example illustrated in FIGS. 2, 3 and 4 can achieve a number of advantages over prior flywheel designs and systems, as discussed below.

[0049] The kinetic energy (KE) of a flywheel is given by the following equation (1):

KE=0.5*I.sub.m (spin axis)*ω.sup.2 (in-lbf)  (1)

where I.sub.m is the mass moment of inertia of the rim about its spin axis, e.g., I.sub.m=I+mr.sup.2, where m is the mass of the rim and r is the radius, and ω is the rotational (angular) velocity. As rotational velocity increases, the radial (centrifugal) force F.sub.r also increases, as given by equation (2).

F.sub.r=m*ω.sup.2*r  (2)

Thus, while dense material can store more energy it is also subject to higher radial force and thus fails at lower rotation speeds than low density material. Therefore, tensile strength tends to be the more important practical design criteria than density of material, which is the reason that known commercial flywheel rims are composed of low density, high strength carbon & glass fiber/epoxy laminates. With the flywheel designs discussed herein, flywheel filler mass design can be implemented to increase mass while maintaining flywheel and rim integrity. For example, if flywheel mass is doubled, I.sub.m is doubled, which according to equation (1) doubles the KE of the flywheel system.

[0050] The total kinetic energy stored (E.sub.k) for a given mass (m.sub.c), is given by equation (3).

E.sub.k=0.5m.sub.cr.sup.2ω.sup.2  (3)

Equation (3) shows that stored energy increases four-fold for each doubling of rotational velocity ω, due to the squared term. Accordingly, if a flywheel design can be implemented that permits reliable operation at higher rotational velocities, the energy storage, and energy density can be significantly increased.

[0051] Radial and hoop rim stresses, as defined by Roark, are a function of radius, r.sup.2, and the radial body force (δ). The radial body force is a function of radial centrifugal force divided by rim geometric volume. The radial force is a function of m, r and ω.sup.2 as indicated by the radial (centrifugal) force equation discussed earlier.

[0052] Using the above equations for calculations, in conjunction with FEA simulations, a number of parametric variations can be studied for optimization. Some such parameters include laminate thickness, laminate mass, lobe configurations including number and geometry of lobes, rim diameters, cost calculations with different configurations to reduce high cost items, e.g., amount of carbon/glass fiber material (T700), complexity and assembly costs, varying fiber angle with respect to radial direction, e.g., 0, 10, 20, 30, 45 degrees, hoop direction, 0, 10, 20, 30, 45 degrees and varying filler mass configuration. The flywheel designs discussed herein adopt criteria for one or more of the above parameters, which may be reviewed in combination, to achieve design goals.

[0053] The flywheel design illustrated in FIGS. 2, 3 and 4 align a majority of the composite fiber with the radial force to take advantage of the higher tensile strength of the fibers in reacting the force under load. Lobes 202 are thus able to withstand increased loading by meeting tensile and compressive forces in alignment with the carbon and/or glass fibers of the composite material. Filler material 204 radially displaces with increasing angular velocity to apply a compressive force on laminate 212 to counteract the radial force acting on the laminate 212 to minimize delamination. This increased capacity for loading, while maintaining a lightweight structure provided by the composite laminate construction, permits a number of design and/or operational options for increasing energy density and/or maximizing rim energy storage capacity. The lobe design permits separation of the rim material from the mass filler material, which obtains several advantages including greater angular velocity, ease of manufacturing and flexibility in design and implementation of the filler mass, to name a few.

[0054] In alternative embodiments, as shown in FIGS. 12a and 12b and FIGS. 13a and 13b, fibers are aligned in the hoop direction, such that the radial displacing masses oriented around the circumference of the hub or at dipole ends displace radially with increasing angular velocity and bear up against the hoop wound laminate to apply a compressive load to minimize laminate thru thickness radial stress to minimize the potential for delamination and therefore rim failure. FIG. 12a shows the rim 1200 at rest with the hub 1201 and 8 filler masses 1202, for this design, although any number of filler masses may be provided, in contact and restrained by the carbon/epoxy laminate 1203. FIG. 12b shows the rim 1210 at design speed with the hub 1211 not in contact with the 8 filler masses 1212, which are restrained by laminate 1213. FIG. 13a shows the dipole rim 1300 at rest with the hub 1301 and 2 filler masses 1302, for this design, although any number of filler masses may be provided, in contact and restrained by the carbon/epoxy laminate 1303. FIG. 13b shows the rim 1310 at design speed with the hub 1311 not in contact with the 2 filler masses 1312, which are restrained by laminate 1313.

[0055] Thus, use of the filler mass in separate lobes or oriented around hub circumference or at dipole ends permits design of compressive forces in the composite loop or hoop wound laminate. The separate masses each react to the applied radial force during operation at a designed angular velocity to apply a compressive force to the composite loop or hoop laminate. For example, at operational rotational velocity, radial stress on an outer end 214, as shown in FIG. 2, of a lobe 202 can urge the laminate layers of casings 212 apart near end 214, ultimately leading to delamination and degradation of the integrity of casings 212 causing rim failure. The filler material 204 or as shown in FIGS. 12a, 12b, 13a and 13b, as 1202, 1212, 1302, 1312, respectively, is specified and designed to apply a compressive force to outer ends 214 of lobes 202 or to 1203, 1213, 1303, 1313 to compress the laminate layers together, even as they experience tensile stress that is reacted well by the fibers in the composite material. The compressive force applied to outer ends 214 of lobes 202 and to 1203, 1213, 1303, 1313 counters the potentially delaminating radial stress on casings 212 and 1203, 1213, 1303, 1313 to contribute to maintaining the mechanical integrity of casings 212, and casings shown in FIGS. 12a, 12b, 13a, and 13b, as 1203, 1213, 1303, 1313, respectively.

[0056] The separate filler material mass can thus be designed to provide a separate compressive force to ends 214, and shown in FIGS. 12a, 12b, 13a, and 13b, as 1203, 1213, 1303, 1313, respectively, of each lobe 202 or laminate 1203, 1213, 1303, 1313 to counteract the through laminate thickness radial tensile force that otherwise cause delamination in prior commercial composite rims, which do not have such radially displacing filler material masses. Since each filler material mass is separate, they can be individually designed for compressive force based on material density, radial position and designed rotational velocity. The filler material mass applies a compressive force to counteract composite laminate thru thickness radial stress. In the absence of such a mass, the rim rotational velocity is limited to a maximum rotation of approximately 15,000 rpm, to avoid delamination of composite laminates with fibers oriented in a circumferential direction.

[0057] Thus, the same radial force that causes prior rim designs to fail is utilized to apply a force to act on a separate mass. In some example implementations, the mass is not separate. The radial force acting on the filler material mass in each lobe 202 applies a compressive force to casing 212 at outer ends 214 to counteract the same thru thickness rim radial force that is acting to separate the hoop laminate of casing 212 at outer ends 214.

[0058] Approximately 70% of the fibers in casing 212 in lobes 202 and in casing 1303,1313 are oriented in the radial direction. This is compared to 100% of the fibers oriented in the hoop direction in casings 1203,1213. According to other examples, the percentage of fibers aligned in the radial direction can be in the inclusive range of from about 25% to about 90%. Fibers oriented in the radial direction directly react the radial force such that, e.g., the relatively weaker composite resin bears less load. The remaining 30% of the fibers in casing 212, a majority of which are located at outer ends 214, transition to or are aligned in the circumferential direction, where the radial stress induced in part by the rotational velocity acts to separate the laminate layers. Alternately, FIGS. 12a and 12b orient load bearing composite fibers in the hoop direction, fibers in the hoop direction can vary from 0 to 45 degrees relative to the longitudinal axis of rotation. Fibers oriented in the hoop direction restrain radial displacing masses oriented around the circumference of the hub. The radial displacing masses apply a compressive load to the hoop wound laminate to minimize the thru thickness radial force acting on the laminate to minimize the potential of delamination.

[0059] The resin matrix (epoxy) in the composite material of casing 212 in FIG. 2, and 1213 and 1313, in FIGS. 12b and 13b, respectively, having a relatively weaker tensile strength than the fibers, experiences increased loading as the radial force on the portions of casing 212, 1213 and 1313 that have fibers oriented in the circumferential direction is reacted. The comparatively weak tensile strength resin matrix can fail sooner in these regions, e.g., outer ends 214 in FIG. 2, and 1314 in FIG. 13b, than does the relatively stronger tensile strength fibers. The thru thickness radial force is increased at greater radial distances, so that outer ends 214 and 1314 experience significant radial stress, even as the weaker composite material bears greater loads.

[0060] The separate mass or variable density filler, being acted upon by the same radial force counteracts the thru thickness force acting on the radial to circumferential directionally transitioning fibers in casing 212 and 1313. The mass of filler material 204 in FIGS. 2 and 1311 in FIG. 13b, acts on the fibers in casing 212 in FIGS. 2 and 1313 in FIG. 13b, at outer ends 214 in FIGS. 2 and 1314 in FIG. 13b, by applying a compressive force that counteracts the radial force acting on the weaker resin matrix in composite casing 212 and 1313. This compressive force contributes to avoiding delamination of casing 212 and 1313 at outer ends 214 and 1314.

[0061] Similarly, as shown in FIG. 12b, the separate mass or 8 variable density fillers, being acted upon by the same radial force counteracts the thru thickness force acting on the hoop oriented fibers in casing 1213. The mass of 8 filler materials 1212 acts on the fibers in casing 1213 by applying a compressive force that counteracts the radial force acting on the weaker resin matrix in composite casing 1213. This compressive force contributes to avoiding delamination of casing 1213.

[0062] As shown in FIGS. 2, 12b, and 13b, by specifying a design rotational velocity, the filler mass density can be specified and designed to apply the desired compressive force to prevent delamination at outer ends 214 and 1314, as well as hoop oriented fibers 1213. The lobe design for flywheel 200, dipole design 1310 and circular design 1210 thus utilizes the tensile strength of the fibers in the composite material to permit significant increases in rotational velocity, while housing mass that contributes to preventing delamination near a flywheel rim. By permitting a significant increase in rotational velocity, significant increases in stored energy density can be achieved, which reduces kW/hr costs. In the case of utilities or other entities that utilize backup energy storage, the present design makes flywheels an affordable option without challenges presented by batteries.

[0063] As shown in FIG. 2, radial forces may also be used to reduce delamination occurrences at the inner ends of lobes 202. Since the inner ends are anchored to hub 208, the radial forces acting on the filler material 204 tends to urge the inner ends of lobes 202 radially outward. This radial outward force is reacted by the mechanism that fastens lobes 202 to hub 208, such as, for example, bolts 210. The reacted radial force applies a compressive force to inner ends of lobes 202 to contribute to preventing delamination in that area, where the relatively weaker resin matrix of the composite material of casings 212 bears greater loading than where the fibers are radially oriented.

[0064] In some example implementations of the flywheel system as shown in FIGS. 2, 12a, 12b, 13a, and 13b, the lobe design of flywheel 200, 1200 and 1300 is better able to retain filler material at a greater radial distance with a greater density than was possible with prior designs. The greater radial distance and density translates to greater energy density in the same amount of space. In some example implementations, the rotational velocity of the flywheel can be significantly increased, leading to a multiple of energy density and storage due to the squared rotational velocity term in the equation for the stored kinetic energy E.sub.k.

[0065] The modular feature of the lobe design offers greater opportunity for maintenance and repair, where a malfunctioning/damaged lobe can be replaced onsite (onboard), while the prior flywheel design would not be replaceable or potentially repairable until the vessel reaches a port with the capacity to provide such services. The lobe, circular and dipole designs can provide higher density energy storage in a smaller space than prior designs, leading to reduced operational space, reduced cost, potentially greater numbers of flywheel systems in a given space, and other such physical advantages. The lobe, circular and dipole designs can take advantage of low cost extrusion and/or pultrusion fabrication processes, which can be implemented in parallel, to speed manufacture and reduce associated costs. The flywheel rim designs discussed herein may be used with current flywheel components, such as motor/generators, radial bearings, magnetic lift systems, so that cost can be reduced for implementation of the new designs.

[0066] As shown in FIGS. 2, 12a, 12b, 13a and 13b, filler and hub material 204, 208, 1202, 1201 and 1302, 1301 can be any type of material that fulfills design specifications, including, but not limited to materials such as elastic resins similar to polyurethane, cement, aluminum and steel. Cement offers greater mass, low strength at low cost, aluminum is useful as a filler material because of its relatively light weight for its rigidity so is high strain to failure resin(s) for its elasticity. Steel represents a greater mass, high strength material also with rigidity properties that are useful in flywheel applications. Composites offer matrix additives to tailor both the mass and stiffness for specific applications.

[0067] The number of loops or lobes may be varied. For example, reducing the number of lobes reduces the amount of expensive fiber in the composite material used to construct the lobes, leading to overall cost savings. A reduction in the number of components can also reduce manufacturing and maintenance costs.

[0068] The loop area subject to radial force may be modified or designed to meet specific criteria, including controlling magnetic bearing parasitic losses. For example, the loop area subject to radial force, as well as the volume of the filler mass, may be reduced by modifying loop cross section dimensions along the length of the radially aligned portions of the loop. FIG. 5 illustrates such a cross section dimension modification in an example using 10 loops to construct a rim. A loop beam 502 extends in the radial direction, and has an angular modification at an angle 504 in the outer radial region that serves to reduce loop cross sectional area, thereby controlling filler material volume and mass. These modifications can be applied to any of the loop/lobe designs discussed herein, for any number of loops/lobes.

[0069] According to some example implementations, the lobes (loops) attached to a hub may be spaced from each other, such that a gap is provided between each lobe. In such examples, the lobes may/may not be provided with lateral support, for example by the presence or absence of circumferentially aligned support members between the lobes. In some examples, the lobes may be provided with a freedom of movement in a circumferential direction, such as by, for example, being permitted to pivot with respect to the hub. In some examples, a filler material or structure may be provided between the lobes, which can contribute to maintaining the position of lobes with respect to each other. The variations or modifications to the lobes and their arrangements can be applied to any of the various examples discussed herein.

[0070] The filler mass composition and disposition can be utilized as a design parameter. For example, the filler material can be any type of useful material including metallic, fiber/matrix composite, polymer or plastic/thermoplastic or cement or combinations thereof, as non-limiting examples. The filler material may be constructed by molding, including injection molding, machining, stamping, 3-D printing and/or other operations that can reduce costs and/or improve quality.

[0071] FIG. 6 is a partial cross-sectional side view of a flywheel rim 600, designed with circular sections radially stacked around the circumference of the rim. Segmented quarter circle or some arc angle aluminum rim inserts 604 are nested between carbon/epoxy rims 602. Inserts 604 are masses that apply a compressive force to rims 602, which tends to balance a radial stress experienced by rims 602. The design of rim 600 can control delamination stresses with the alternating layers of inserts 604 and rims 602. Aluminum inserts 604 can vary in radial thickness to optimize the compressive force applied to the adjacent outer radial composite rim.

[0072] FIGS. 7 and 8 provide alternate lobe designs that align mass with radial aligned carbon fiber/epoxy laminates. Rims 700 and 800 have end caps 702, 802 may be comprised of, among other materials, aluminum, steel, polymer or hybrid that are secured, assemblies which, once assembled, geometrically secure, or lock the mass structure to the carbon/epoxy beams 701, 801. Rim 700 utilizes the volume between the radial beams to house filler material. Rim 800 aligns the mass of the aluminum end caps directly along the center line of the beams. The designs of rims 700 and 800 exploit the alignment of fiber tensile strength in the radial direction and locate end caps at a greater radial distance from the rotating axis. Radial stress is observed in the outer radial areas of the composite beams near the end curvature. This radial stress is a thru thickness tensile stress, which can be controlled with bolt tension applying a compressive force to the beam end curvature. Bolt torque would be dependent on designed rotational velocity. Hoop oriented fibers can be wound around the circumference of 700 to reduce end cap stress. The end caps apply a compressive load to the laminate to reduce thru thickness laminate radial stress.

[0073] FIG. 9 is a partial isometric view of a 10 lobe flywheel rim 900 with a full length sprocket hub. The sprocket hub interacts with each loop inner axle extension component to react motor/generator torque stresses. Rim 900 includes a hub hoop band 902 that can contribute to relieving inner axle, fastener (hub to lobe) and lobe stress.

[0074] FIG. 10 is an isometric view of an eight lobe flywheel rim 1000 with a filler material. Rim 1000 includes end hubs combined with a central sprocket hub. With the design of rim 1000, the radial deformation is excellent as it reduces metallic component flexure stress, hub reaction stresses and reduces laminate cyclic fatigue over the operational life of the rim. The design of rim 1000 uses a “semi-loop” geometry concept, where the rim is divided into 8 “loop-like” sections 1001, although any number of sections 1001 may be provided, that are bonded together and this sub-assembly then undergoes exterior hoop carbon fiber filament winding 1002. Filament winding binds the “loop-like” sections into a unified rim structure 1000. This construction results in comparatively low stresses on the central sprocket hub. This design extends the central sprocket hub full length and utilizes end hub integration to effectively react flexure. The design controls axial deflection well, which reduces component/assembly stress, a target for reducing the impact of cyclic fatigue. Although the component count of this design may be considered high, the components have simple 2D geometric cross sections permitting low-cost fabrication by extrusion or pultrusion. The concepts shown for rim 1000 are readily transferable to other rim implementations to reduce rim component stresses. Rim 1000 may be implemented with an axially oriented carbon fiber-epoxy composite inner axle component.

[0075] FIG. 11 is an isometric view of an eight lobe flywheel rim 1100 that utilizes the loop geometry to integrate the loop into a central hub-like structure eliminating a central hub. Rim 1100 can orient from approximately 4 to 90 degree or variations as shown by 1101, or from approximately 8 to approximately 45 degree or variations, to secure loop structures around a central rotating axis. Securing the 4-90 degree structures is a hoop wound laminate 1102. The design of rim 1100 permits the loop to deform somewhat independently along loop axial length. This design builds elasticity into the carbon-epoxy material system.

[0076] This design, as shown in FIG. 11, permits the offsetting of filler rim mass to either side of the radially aligned carbon-epoxy fibers 1103. In other examples discussed herein, the load bearing hoop wound carbon fiber 1104 is directed around the filler mass, resulting in transfer of the metallic load to the carbon fiber. In the design of rim 1100, increases in the radial load are directly reacted by the radially aligned carbon fiber 1103 and 4-90 degree structures 1101, 1102. The filler masses are positioned to either side of this load bearing radially aligned fiber 1103 which is out of the load path, thus reducing metallic component stress. This design offers a moderate component count and simplified geometric load path, which is important from a stress perspective. Hoop oriented fibers can be wound around the circumference to increase the axial bending rigidity of rim 1102.

[0077] The flywheel rim design 1200, 1210, as shown in FIGS. 12a and 12b, respectively, illustrate how the radial mass(es) are displaced. The fiber orientation of the rim shown in FIGS. 12a and 12b may be oriented in the radial (loop design) and/or hoop direction, as illustrated in the hoop direction. FIG. 12a illustrates a flywheel rim at rest. The components of the rim are the outer carbon/epoxy laminate 1203, and for this example eight radially displacing mass(es) 1202 located around the rotating axis central hub 1201. Referring to FIG. 12b, as the flywheel rim rotational velocity increases, the mass(es) continue to radially displace until the flywheel rim reaches its design angular speed. At design speed, the radial mass(es) are at their maximum radial displacement 1212. Each filler mass theoretically radially displaces the same distance 1214. This is illustrated in FIG. 12b by a gap, or space 1214, disposed between the rotating hub and rotating mass(es). The radial displacing mass(es) may remain in contact with the hub, elastic filler material, or may not remain in contact with the hub, inelastic filler material, as illustrated. In the latter case, hub and filler mass geometry are designed to permit contact in the hoop direction for the transfer of rim rotational torque loads between the hub and filler mass(es). Similarly, as shown in FIG. 13b, the dipole design 1310 radial displacing masses 1312 at design speed may or may not exhibit a gap or space 1315.

[0078] The radial displacing mass(es) can be any number around the hub perimeter, any size and/or geometric shape. As shown in FIG. 2, the radial displacing mass(es) has an inner portion 215 and an outer portion 216. Inner portion 215 is disposed opposite to the outer portion 216. Inner portion 215 is adjacent to the hub perimeter and the outer portion 216 is adjacent to fiber resin composite. Radially positioning the outer portion 216 further from the rotating axis significantly increases the rims mass moment of inertia thereby significantly increasing total kinetic energy stored. The mass could be a single component or multiple components located around the hub. A single mass can consist of a single component or an assembly of components. The mass(es) can utilize an infinite range of materials from fibrous/matrix materials, metals, hybrid metallic/fibrous materials, pressed powders, high strain to failure resin(s), cement any material that permits the radial force to act on the mass to apply a compressive force to the laminate that minimizes delamination.

[0079] The joint between the radial displacing mass(es) and the hub also has an infinite number of geometric possibilities. This joint reacts flywheel rim torque during acceleration/deceleration, as well as to permit each mass to radial displace to apply a compressive load/mass on the hoop wound carbon fiber/matrix laminate and maintain a balanced rim.

[0080] The hub interacts with the motor/generator and the radial displacing mass(es). As with the radial displacing mass(es), the hub has an infinite number of geometric possibilities and material options. Hub geometry and material selection needs to react motor/generator torque, permit a mass/each mass to radially displace and maintain a balanced rim.

[0081] As illustrated in FIGS. 12a and 12b, and FIGS. 13a and 13b, as the flywheel rim increases in rotational velocity the radial mass(es) may or may not remain in contact with the hub, contact is determined by the filler mass material elasticity. With respect to loop type rims, the radial masses may remain in contact with the rim. For hoop wound laminates, as shown in FIGS. 12a and 12b, and FIGS. 13a and 13b, radial displacing masses are in contact with the hub at rest. However, with increasing rotational velocity the radial force acts on each mass radially displacing the mass, so that at design speed each mass may no longer contact the hub in the radial direction, but remains in contact with the hub in the hoop direction. At flywheel rim design speed the hub may rotate without radial contact with the mass(es).

[0082] The methods, systems, and devices discussed above are examples. Various configurations may omit, substitute, or add various procedures or components as appropriate. For instance, in alternative configurations, the methods may be performed in an order different from that described, and that various steps may be added, omitted, or combined. Also, features described with respect to certain configurations may be combined in various other configurations. Different aspects and elements of the configurations may be combined in a similar manner. Also, technology evolves and, thus, many of the elements are examples and do not limit the scope of the disclosure or claims.

[0083] Specific details are given in the description to provide a thorough understanding of example configurations (including implementations). However, configurations may be practiced without these specific details. For example, well-known processes, structures, and techniques have been shown without unnecessary detail to avoid obscuring the configurations. This description provides example configurations only, and does not limit the scope, applicability, or configurations of the claims. Rather, the preceding description of the configurations provides a description for implementing described techniques. Various changes may be made in the function and arrangement of elements without departing from the spirit or scope of the disclosure.

[0084] Also, configurations may be described as a process that is depicted as a flow diagram or block diagram. Although each may describe the operations as a sequential process, many of the operations can be performed in parallel or concurrently. In addition, the order of the operations may be rearranged. A process may have additional stages or functions not included in the figure.

[0085] Having described several example configurations, various modifications, alternative constructions, and equivalents may be used without departing from the spirit of the disclosure. For example, the above elements may be components of a larger system, wherein other structures or processes may take precedence over or otherwise modify the application of the invention. Also, a number of operations may be undertaken before, during, or after the above elements are considered. Accordingly, the above description does not bound the scope of the claims.

[0086] A statement that a value exceeds (or is more than) a first threshold value is equivalent to a statement that the value meets or exceeds a second threshold value that is slightly greater than the first threshold value, e.g., the second threshold value being one value higher than the first threshold value in the resolution of a relevant system. A statement that a value is less than (or is within) a first threshold value is equivalent to a statement that the value is less than or equal to a second threshold value that is slightly lower than the first threshold value, e.g., the second threshold value being one value lower than the first threshold value in the resolution of the relevant system.