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US 2013/0192219A1 Aug.1,2013 terminusoftheannularmember32extendsaroundthemiddle rings 42a and 42b. In an exemplary embodiment, the middle rings42aand42bare?xedlycoupledtooneanother.A top ring 44 (FIG. 3) may be coupled to, and extend around, the upper portion of the turbine Wheel 36, With the top ring 44 beingpositionedsothatthecap30oftheradialturbinesystem 12 extends around the top ring 44. [0024] ApluralityofloWerturbineblades48maybe coupledtothebasering40,andtotheloWer,middlering42a. The loWer turbine blades 48 may extend axially betWeen the base ring 40 and the middle ring 42a. The loWer turbine blades 48 may be spaced around the turbine Wheel 36, col lectively de?ning a generally circular roW of blades there around. Similarly, a plurality ofupper turbine blades 50 may becoupledtotheupper,middlering42bandtothetopring44 (FIG. 3). The upper turbine blades 50 may extend axially betWeen the middle ring 42b and the top ring 44. The upper turbine blades 50 may also be spaced around the turbine Wheel 36, collectively de?ning a generally circular roW of bladestherearound.A horizontally-extendingplane46may bede?nedbetWeenthemiddlerings42aand42b,andmay be perpendicular to the vertically-extending center axis 26. In one ormore embodiments, theloWerturbineblades 48 may be identical to the upper turbine blades 50, having the same radialandangularorientationastheupperturbineblades50, but at a different axial location relative to the center axis 26. [0025] ApluralityofloWerradialnoZZlevanes52maybe coupledtotheannulardiskmember 34bofthebase34,andto theradially-inwardterminusportionofthecurvedtransition portion320oftheannularmember 32.ThepluralityofloWer radialnoZZlevanes52may extendaxiallybetWeenthebase 34 and the annular member 32, With the loWer radial noZZle vanes 52 being radially positioned outside of the loWer tur bine blades 48 and spaced circumferentially therearound. Similarly,apluralityofupperradialnoZZlevanes54may be coupled to the angled transition portion 32f of the annular member 32, and to the cap 30. The upper radial noZZle vanes 54 may extend axially betWeen the annular member 32 and the cap 30 (FIG. 3), With the upper radial noZZle vanes 54 beingradiallypositionedoutsideoftheupperturbineblades 48. The loWer radial noZZle vanes 52 may be identical to the upper radial noZZle vanes 54. [0026] Inoneormoreembodiments,theupperandloWer noZZlevanes52,54may bedisposedatananglerelativetoa radius extending from the shaft 38. In one or more embodi ments, the angles of the upper and loWer noZZle vanes 52, 54 may be substantially equal, as can be best appreciated from FIG. 2. Furthermore, in one or more embodiments, from the perspectiveof?uidtravellingthroughthe?oWpassage62a-d, the upper and loWer noZZle vanes 52, 54 may be identical to eachother,asdescribedaboveWithreferencetotheupperand loWer turbine blades 48, 50. Additionally, in an exemplary embodiment, the upper and/or loWer radial noZZle vanes 52, 54may havearelativelyhighloadingcoe?icient,ontheorder ofaZWeifelnumberrangingfromabout 1toabout 1.2.As the term is used herein, ZWeifel number refers to the ratio of tangentialforcesusedasaninitialestimateindeterminingthe minimum solidity and number of the upper and/or loWer radial noZZle vanes 52, 54. [0027] A plurality of loWer turning vanes 56 may be coupled to, and extend around, the turbine Wheel 3 6. In one or more embodiments, each loWer turning vane 56 may include multiple arcuate segments or may be a single annular vane. The loWer turning vanes 56 may be disposed atgenerally the same axiallocationastheloWerturbineblades48,andposi tioned radially betWeen the turbine Wheel 36 and the loWer turbine blades 48. The loWer turning vanes 56 may cascade vertically, and may be adapted to turn the motive ?uid ?oW from a radial direction to an axial direction, and vice versa. Similarly, a plurality of upper turning vanes 58 may be coupled to, and extend around, the turbine Wheel 36. The upperturningvanes58maybedisposedatgenerallythesame axial location as the upper turbine blades 50, and positioned radially betWeen the turbine Wheel 36 and the upper turbine blades50.Theupperturningvanes58may cascadevertically, andmay beadaptedtoturnthedirectionofmotive?uid?oW from an axial direction to a radial direction, and vice versa. [0028] Apluralityofsupportposts60mayextendaxially betWeen the cap 30 (FIG. 3) and the upper, outer angularly extending portion 32d of the annular member 32, proximal theradialport13.The supportposts60may be spacedaround the vertically-extending center axis 26. The support posts 60 may be elongated, tapered aerofoils, for example, or may be simple cylinders or rectilinear supports, as shoWn. In one or more embodiments, the support posts 60 may instead be a screen or the like. [0029] A ?oWpassage62a-dincludingaloWeraxial?oW portion 6211, a loWer radial ?oW portion 62b, a middle axial ?oW portion620,andanupperradial?oW portion62dmay be de?ned by the radial turbine system 12. The loWer axial ?oW portion 6211 may be de?ned betWeen a radially-outWard ter minus of the loWer disk 34a and a loWer end of the loWer, outerangularly-extendingportion32aoftheannularmember 32.TheloWerradial?oW portion62bmay bede?nedbetWeen the annular disk member 34b and the loWer, inner angularly extending portion 32b ofthe annular member 32. The middle axial ?oW portion 620 may be de?ned betWeen the turbine Wheel 36 and the upper and loWer turbine blades 48 and 50. Theupperradial?oW portion62dmay bede?nedbetWeenthe cap 30 (FIG. 3) and the upper, inner angularly-extending portion 32e ofthe annular member 32, and may extend from the radial port 13 radially toWard the turbine Wheel 36. The upperradial?oW portion62dmay beaxiallyspacedfromthe loWer radial ?oW portion 62b. The middle axial ?oW portion 620may beradiallypositionedbetWeentheshaft38andeach oftheradial?oW portions 62b and 62d. The loWerradial?oW portion 62b may be in ?uid communication With the middle axial?oW portion620,Whichmay bein?uidcommunication With the upper radial ?oW portion 62d. The loWer axial ?oW portion 6211 may be axially positioned betWeen the loWer radial ?oW portion 62b and the Wave chamber 22, radially positioned so that the loWer radial ?oW portion 62b may be radiallypositionedbetWeenthemiddleaxial?oWportion620 and the loWer axial ?oW portion 62a. The loWer radial ?oW portion 62b may be in ?uid communication With the loWer axial?oW portion62a,Whichmay bein?uidcommunication With the Wave chamber 22. [0030] Inoneormoreembodiments,theWavechamber22 may be in?uid communication With a ?uidic environment 64 via the ?oW passage 62a-d. The ?uidic environment 64 may be contained in an expandable bladder (not shoWn), other structures (not shoWn), or may be the ambient atmosphere surroundingtheradialturbinesystem12.Moreover,bi-direc tionalmotive ?uid ?oW betWeen theWave chamber 22 and the ?uidic environment 64 is permitted via the ?oW portions 62a-d, as indicated by the bi-directional arroWs designating theloWeraxial?oW portion62a,theloWerradial?oW portionPDF Image | ENERGY CONVERSION SYSTEM WITH RADIAL FLOW TURBINE
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