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US 2013/0192219Al Aug.1,2013 motive?uidsubstantiallywithoutswirl,i.e.,inaradialdirec tion without a signi?cant circumferential component. The motive?uid?ow throughtheturbineblades50furthercauses the turbine blades 50, and thus the turbine wheel 36, to con tinuetorotatearoundthevertically-extendingcenteraxis26. As a result, the shaft 38 rotates. The lower turbine blades 48 andtheupperandlowerturningvanes56and58alsocontinue to rotate along with the turbine wheel 36 and the shaft 38. In one or more other embodiments, however, the upper and lower turning vanes 56, 58 may remain stationary with respect to the rotating shaft 38 and turbine wheel 36. [0041] After?owingpasttheupperturbineblades50,the motive ?uid ?ows radially-outward, increasing in radius toward the upper radial noZZle vanes 54 via the upper radial ?ow portion 62d. In an exemplary embodiment, the ?ow area intheupperradial?ow portion62dmay beconstant,similar to the described lower radial ?ow portion 62b, and thus the motive ?uidmay notundergo any signi?cantchange inradial velocitywhile?owingthroughtheradial?owportion62d.In anexemplaryembodiment,whentheradialturbinesystem12 isrunningwithoff-designvelocityratiosand/oroff-design runningconditions,anyswirlleftintheair?ow intheupper radial?ow portion62dmay bereducedduetothefreevortex ?ow, achieving at least some degree of diffusion and e?i ciency-enhancementfortheoff-designvelocityratiosand/or off-designrunningconditions. [0042] Duringitsradialoutward?owthroughtheradial ?ow portion62dofthe?ow passage62,themotive?uidmay ?ow between the upper radial noZZle vanes 54, and any tan gential component of its velocity may slow for the same reason itpreviously accelerated from C lto C2. This decelera tion reduces drag losses experienced in the reverse oriented upper radial noZZle vanes 54. Further, the reduced swirl and thelargeexitangleofeachoftheupperradialnoZZlevanes54 minimiZes pressure loss due to incidence effects and turning ofthemotive?uidduringits?ow betweentheupperradial noZZle vanes 54. After exiting the upper radial noZZle vanes 54, the motive ?uid may continue to ?ow radially-outward, exitingtheradialturbinesystem12andbeingdischargedinto the environment 64. [0043] Thereverseorback?owoftheenergyconversion system10occurswhentheOWC 14falls,decreasingthe pressure in the wave chamber 22. As a result of the drop in wave chamber 22 pressure, the motive ?uid may be drawn intotheradialturbinesystem12fromthe?uidicenvironment 64, and expelled therefrom into the wave chamber 22. As such,themotive?uidmay entertheupperradial?ow passage 52d, viatheradialport13,may be swirledby theupperradial noZZle vanes 54. For example, the upper radial noZZle vanes 54 may be angled to impart the same swirl direction at sub stantiallythesameexitswirlangle(x1(FIG.4)asimpartedby the lower radial noZZle vanes 52. The motive ?uid may then engagetheupperturbineblades50,beturnedbytheturning vanes 58 in the axial ?ow passage 62c, engage the lower turbine blades 48, ?ow radially outward through the lower radial ?ow portion 62b, and then through the lower radial noZZle vanes 52, and ultimately back out through the axial ?ow portion 62a and into the chamber 22. [0044] Asaresultofthisdescribedsymmetric?owpath design, the upper and lower turbine blades 48 and 50, the upper and lower radial noZZle vanes 56 and 58, the turbine wheel36,and/ortheshaft38may continuetooperateregard lessofwhetherthe?ow isfromthewavechamber22ortoit, thereby supplying continuous rotational shaft energy to the generator16,oranotherdevice.Theradialturbinesystem12 canthusbedescribedasaself-rectifyingradial?ow turbine, providingunidirectionalrotationoftheshaft38inresponseto altemating“forward”and“reverse”(i.e.,bi-directional)?ow throughthe?ow passage62asindicatedbyarrows66and68 in FIG. 3. [0045] Duringtheexemplaryoperationoftheenergycon version system 10, due at least in part to the above-described symmetricradial?owpathdesignoftheradialturbinesystem 12, the use of inter-blade row free-vortex sections are allowed tobeusedtomaximum advantage.Moreover,thepureradial ?ow that the motive ?uid undergoes during the operation of the energy conversion system 10 allows the use of two-di mensional blade shapes without any performance penalty; there are no three-dimensional effects or radial ?ow varia tions that would be otherwise present in an axial or mixed ?ow device.Further,theradialin?ow ofmotive?uidinto,and the radial out?ow of motive ?uid from, the radial turbine system 12 allows for an axially compact design that can be readilyoverhungfromtheshaft38.Stilfurther,sincemotive ?uid?ows intoandoutoftheradialturbinesystem12radially and perpendicular to the center axis 26, access to the genera tor 16 and mechanical components such as bearings and/or seals is facilitated. Moreover, the radial turbine system 12 provides a wider range of practical turbine blade hub to tip ratios, which facilitates the scaling of the radial turbine sys tem 12 to commercial siZes. [0046] FIGS.5and6illustrateanexemplaryenergycon version system 70, according to one or more embodiments, which may be similar to one or more embodiments of the energy conversion system 10 described above with reference to FIGS. 1-4. The energy conversion system 70, however, may include a base block 72 on which the generator 16 may be coupled and/or mounted. The base block 72 and the gen erator16may behorizontallyoriented,suchthattheshaft38 (FIGS. 2 and 3) extends horizontally, rather than vertically. The generator 16 may be operably coupled to a radial turbine system 74, which is similar to the radial turbine system 12 described above with reference to FIGS. 1-4, except that the plurality of lower radial noZZle vanes 52 and lower axial portion6211may beomittedandreplacedwithascrollduct76 that is coupled to the annular housing 28. Although not shown, in one or more other embodiments, the lower radial noZZle vanes 52 and/or the lower radial portion 6211 may be retained, with the scroll duct 76 augmenting the swirling effect of the lower radial noZZle vanes 52. The scroll duct 76 de?nesascroll?ow passage76a,whichmay be,forexample, volute shaped. Although not shown, the scroll ?ow passage 7611 may be in ?uid communication with the radial ?ow portion 62b ofthe ?ow passage 62, and with the wave cham ber22. [0047] Inexemplaryoperation,withcontinuingreference to FIGS. 1-6, wave motion occurs in the ocean 18, thereby causingtheOWC 14tooscillate,thatis,riseandfal,within thewavechamber22.WhentheOWC 14rises,motive?uid such as, for example, air, within the wave chamber 22 is compressed,causingthemotive?uidto?owupwardlyinthe wave chamber 22 and into scroll?ow passage 76a de?ned by thescrollduct76.Themotive?uidcontinuesto?ow through scroll ?ow passage 76a, with the scroll ?ow passage 76a causingthemotive?uidtoswirland?ow axiallytowardsthe radialturbinesystem74.The swirlingairexitsthescroll?owPDF Image | ENERGY CONVERSION SYSTEM WITH RADIAL FLOW TURBINE
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