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US 2013/0192219A1 Aug.1,2013 passage76aand?oWs intotheradial?oW portion62bofthe ?oW passage 62. The motive ?uid continues to sWirl and ?oW radially-inWard toWards the inlet of the turbine blades 48 via theloWerradial?oW portion62bofthe?oW passage62.Thus, the initial sWirl generation of the motive ?uid ?oW may be accomplishedWiththescroll?oW passage7611insteadofWith the omitted noZZle vanes 52. The remainder of the operation may be substantially the same as that described above With respect to the energy conversion system 10, With the ?oW proximalthechamber22beingthroughthescroll76instead oftheloWeraxial?oW passage62a. [0048] InvieWoftherespectiveoperationsoftheenergy conversion systems 10 and 70, as described above, it is clear that the energy conversion systems 10 and/or 70 are easily adaptable to a vertical orientation, a horiZontal orientation, and/or any combination thereof, and can take advantage of scroll-styleinletand/ordischargeducting. [0049] FIG.7illustratesanexemplarymethod84ofrotat ingashaft.Themethod84may includepartiallysubmerging astructureinabody ofWatertoform aWave chamber, asat86. Themethod84may alsoincludepermittingamotive?uidto ?oWoutoftheWavechamberasat88.Themethod84may proceedtodirectingthemotive?uidina?rstradialdirection, as at 90, and sWirling the motive ?uid during directing the motive ?uid in the ?rst radial direction and betWeen a ?rst pluralityofturbinebladescoupledtotheshaft,asat92.The method84may alsoincludeturningthemotive?uidfromthe ?rst radial direction to a ?rst axial direction, as at 94, and turning the motive ?uid from the ?rst axial direction to a second radial direction that is substantially opposite to the ?rst radial direction, as at 96. In one or more embodiments, the method 84 may include directing the motive ?uid in the second radial direction and betWeen a second plurality of turbine blades coupled to the shaft, as at 98, and rotating the shaft, as at 100 by directing the motive ?uid in the ?rst radial directionandbetWeenthe?rstpluralityofturbineblades,and bydirectingthemotive?uidinthesecondradialdirectionand betWeenthesecondpluralityofturbineblades. [0050] Although the present disclosure has described embodimentsrelatingtospeci?cturbomachinery,itisunder stood that the apparatus, systems and methods described herein could applied to other environments. For example, according to other exemplary embodiments, instead of, or in additiontoWave energy sources, otherenergy sources may be con?gured to be used With embodiments of the radial turbine systems described above. For another example, according to other exemplary embodiments, instead of, or in addition to a generator, embodiments of the radial turbine systems describedabovemay beusedasdriversforothermechanical devices that require shaft poWer input such as compressors or pumps. In several exemplary embodiments, various horiZon tal and/or vertical arrangements of the embodiments of the radial ?oW turbine systems and generators described above may be implemented invarious installations. [0051] The foregoing has outlined features of several embodiments sothatthoseskilledintheartmay betterunder stand the present disclosure. Those skilled in the art should appreciatethattheymay readilyusethepresentdisclosureas a basis for designing or modifying other processes and struc tures for carrying out the same purposes and/or achieving the same advantages of the embodiments introduced herein. Those skilled in the art should also realiZe that such equiva lent constructions do not depart from the spirit and scope of the present disclosure, and that they may make various changes, substitutions and alterations herein Without depart ingfromthespiritandscopeofthepresentdisclosure. 1. A collection apparatus for a separator, comprising a housingatleastpartiallyencirclinga?oW separationpassage and de?ning a chamber and a cutout, the chamber being in ?uid communication With the ?oW separation passage to receive a separated ?oW therefrom, and the cutout extending outWard from the chamber to at least partially de?ect the separated?oW. 2. The energy conversion system of claim 1, Wherein the ?rst radial ?oW passage increases in axial thickness While decreasing in radius, and the second radial ?oW passage decreases in axial thickness While increasing in radius, such that the ?rst and second radial ?oW passages each have a substantiallyconstantcross-sectional?oW area. 3. The energy conversion system of claim 1, Wherein the ?rst and second radial ?oW passages and the axial ?oW pas sage are con?gured to channel the ?uid bi-directionally therein. 4. The energy conversion system of claim 1, Wherein the annularmember comprises top and bottom members extend ing radially from a point proximate the turbine Wheel, the bottommember atleastpartiallyde?ningthe?rstradial?oW passage and the top member at least partially de?ning the secondradial?oW passage. 5. The energy conversion system of claim 1, Wherein the ?rst and second exit sWirl angles are oriented in the same circumferential direction. 6. The energy conversion system of claim 1, Wherein the ?rst and second pluralities of noZZle vanes are each offset from the shaft by a radial distance, the radial distance of the ?rstpluralityofnoZZlevanesbeingsubstantiallyequaltothe radial distance of the second plurality of noZZle vanes. 7. The energy conversion system of claim 6, Wherein the ?rst and second pluralities of noZZle vanes are each oriented at an angle With respect to a radius extending from the shaft, theangleofthe?rstpluralityofnoZZlevanesbeingsubstan tially equal to the angle of the second plurality of noZZle vanes. 8. The energy conversion system of claim 1, Wherein the ?rst exit sWirl angle is from about 20 degrees to about 30 degreesandthesecondexitsWirlangleissubstantiallyequal tothe?rstexitsWirlangle. 9. The energy conversion system of claim 1, Wherein: the?rstpluralityofimpulsebladesextendsatleastpartially throughthe?rstradial?oW passage; the turbine Wheel further comprises a second plurality of impulse blades disposed around the shaft, the second plurality of impulse blades extending at least partially though the second radial ?oW passage; and the?rstandsecondpluralitiesofimpulsebladeseachbeing offset from the shaft by a radial distance, the radial distance of the ?rst plurality of impulse blades being substantially equal to the radial distance of the second pluralityofimpulseblades. 10.Theenergyconversionsystemofclaim9,Whereineach bladeofthe?rstandsecondpluralitiesofimpulsebladeshas aturningangleoffromabout50degreestoabout70degrees. 11. The energy conversion system of claim 1, Wherein the ?rst plurality of noZZle vanes is radially-offset from the shaft by a ?rst distance and the ?rst plurality of impulse blades is radially-offset from the shaft by a second distance, Wherein the ?rst distance is about tWice the second distance.PDF Image | ENERGY CONVERSION SYSTEM WITH RADIAL FLOW TURBINE
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