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US 2004/0088985 A1 May 13,2004 circumferentially disposed nozzle elements 43. The radial extent of the nozzles 43 are de?ned by an inner radius R1 and an outer radius R2 as shoWn. It Will be seen that the individual noZZle elements 43 are relatively short With quickly narroWing cross sectional areas from the outer radiusR2totheinnerradiusR1.Further,thenoZZleelements are substantially curved both on their pressure surface 44 and their suction surface 46, thus causing a substantial turning of the gases ?owing therethrough as shoWn by the arroW. [0039] The advantage of the above described noZZle design is that the overall machine siZe is relatively small. Primarily for this reason, most, ifnot al,noZZle designs for turbine application are of this design. With this design, hoWever, there are some disadvantages. For example, noZZle ef?ciency suffers from the noZZle turning losses and from exit ?oW non uniformities. These losses are recogniZed as beingrelativelysmallandgenerallyWellWorththegainthat is obtained from the smaller siZe machine. Of course itWill be recogniZed that this type of noZZle cannot be reversed so as to function as a diffuser With the reversal of the How direction since the How Will separate as a result of the high turning rate and quick deceleration. [0040] ReferringnoWtoFIG.7B,thenoZZlearrangement of the present invention is shoWn Wherein the impeller 42 is circumferentially surrounded by a plurality of noZZle ele ments 47. It Will be seen that the noZZle elements are generally long, narroW and straight. Both the pressure sur face 48 and the suction surface 49 are linear to thereby providerelativelylongandrelativelysloWlyconverging ?ow passage 51. They include a cone-angle Within the boundaries of the passage 51 at preferably less then 9 degrees, and, as Will been seen, the center line of these cones as shoWn by the dashed line, is straight. Because of the relativelylongnoZZleelements47,theRZ/R1ratioisgreater then 1.25 and preferably in the range of 1.4. [0041] Because of the greater RZ/R1 ratio, there is a modest increase in the overall machine siZe (i.e. in the range of 15%) over the conventional noZZle arrangement of FIG. 7A. Further, since the passages 51 are relatively long. the friction losses are greater than those of the conventional noZZles of FIG. 7A. HoWever there are also some perfor mance advantages With this design. For example, since there are no turning losses or exit ?oW non-uniformities, the noZZle ef?ciency is substantially increased over the conven tional noZZle arrangement even When considering the above mentioned friction losses. This ef?ciency improvement is in the range of 2%. Further, since this design is based on a diffuserdesign,itcanbeusedinareversed?oW directionfor applications as a diffuser such that the same hardWare can be used for the dual purpose of both turbine and compressor as described above and as Will be more fully described here inafter. [0042] Ifthesameapparatusisusedforanorganicrankine cycle turbine application as for a centrifugal compressor application, the applicants have recogniZed that a different refrigerant must be used. That is, if the knoWn centrifugal compressor refrigerant R-134a is used in an organic rankine cycle turbine application, the pressure Would become exces sive. That is, in a centrifugal compressor using R-134a as a refrigerant, the pressure range Will be betWeen 50 and 180 psi, and if the same refrigerant is used in a turbine applica tion as proposed in this invention, the pressure Would rise to around 500 psi, Which is above the maximum design pres sure of the compressor. For this reason, ithas been necessary for the applicants to ?nd another refrigerant that can be used for purposes of turbine application. Applicants have there fore found that a refrigerant R-245fa, When applied to a turbine application, Will operate in pressure ranges betWeen 40-180 psi as shoWn in the graph of FIG. 8. This range is acceptable for use in hardWare designed for centrifugal compressor applications. Further, the temperature range for such a turbine system using R-245fa is in the range of 100-200° E, which is acceptable for a hardWare system designedforcentrifugalcompressoroperationWithtempera tures in the range of 40-110° F. ItWill thus be seen in FIG. 8 that air conditioning equipment designed for R-134a can be used in organic rankine cycle poWer generation applica tions When using R-245fa. Further, ithas been found that the same equipment can be safely and effectively used in higher temperatures and pressure ranges (e.g. 270° and 300 psia are shoWn by the dashed lines in FIG. 8), thanks to extra safety margins of the existing compressor. [0043] Havingdiscussedtheturbineportionofthepresent invention, We Will noW consider the related system compo nents that Would be used With the turbine. Referring to FIG. 9, the turbine Which has been discussed hereinabove is shoWnat52asanORC turbine/generator,Whichiscom merciallyavailableasaCarrier19XR2 centrifugalcompres sorWhichisoperatedinreverseasdiscussedhereinabove. The boiler or evaporator portion of the system is shoWn at 53 for providing relatively high pressure high temperature R-245fa refrigerant vapor to a turbine/generator 52. In accordance With one embodiment of the invention, the needs of such a boiler/evaporator may be provided by a commer ciallyavailablevaporgeneratoravailablefromCarrierLim ited Korea With the commercial name of 161B. [0044] Theenergysourcefortheboiler/evaporator53is shoWn at 54 and can be of any form of Waste heat that may normally be lost to the atmosphere. For example, itmay be a small gas turbine engine such as a Capstone C60, com monly knoWn as a microturbine, With the heat being derived from the exhaust gases of the microturbine. It may also be alargergasturbineenginesuchasaPratt& WhitneyFT8 stationarygasturbine.AnotherpracticalsourceofWasteheat is from internal combustion engines such as large recipro cating diesel engines that are used to drive large generators and in the process develop a great deal of heat that is given off by Way of exhaust gases and coolant liquids that are circulated Within a radiator and/or a lubrication system. Further, energy may be derived from the heat exchanger used in the turbo-charger intercooler Wherein the incoming compressed combustion air is cooled to obtain better ef? ciencyandlargercapacity. [0045] Finally,heatenergyfortheboilermaybederived from geothermal sources or from land?ll ?are exhausts. In these cases, the burning gases are applied directly to the boiler to produce refrigerant vapor or applied indirectly by ?rst using those resource gases to drive an engine Which, in turn, gives off heat Which can be used as described herein above. [0046] Aftertherefrigerantvaporispassedthroughthe turbine 52, it passes to the condenser 56 for purposes of condensing the vapor back to a liquid Which is then pumped by Way of a pump 57 to the boiler/evaporator 53. Condenser 56 may be of any of the Well knoWn types. One type that is found to be suitable for this application is the commercially available air cooled condenser available from Carrier Cor poration as model number 09DK094. A suitable pump 57 has been found to be the commercially available as the Sundyne P2CZS.PDF Image | ORGANIC RANKINE CYCLE WASTE HEAT APPLICATIONS
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