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ReferringstiltoFIG.3,thecompressor106hasanend390 operativelyconnectedtothealternator108viarotorshaft110 for rotation thereWith. The compressor 106 has a loW-pres sure face 392 and a high-pressure face 394. The high-pressure face 394 faces toWard the compressor inlet 270. The loW pressure face 392 is on an opposite side of the high-pressure face 394, and faces toWard the rotor cavity. As the Working ?uid ?oWs to the compressor 106 as indicated by arroW 120 and passes over the compressor 106, the compressor 106 rotates and compresses the Working ?uid. The Working ?uid passes across the compressor 106 and into compressor cavity 278.As ?uidpassesoverthecompressor106,ispassesalong the high-pressure face 394 and along the loW-pressure face 392. 10 associated thrust to the thermodynamic system, preferably near or to Zero, is referred to as “thrust balancing” across the compressor. Preferably, the pressures are suf?ciently bal ancedtopreventfailures,reducelossesand/orenhanceopera tion. The vanes 496 and/or ridges 498 preferably pump the Working ?uid aWay from the seal 18219 as it ?oWs past the compressor 106. Preferably, the compressor 106 pumps the Working ?uid in a manner that reduces leakage through seal 1821) and/or reduces forces on the rotor shaft. Depending on theparameters(e.g.,type,measurements,etc.)oftheWorking ?uid, the pressure in the compressor cavity 278 may be suf ?ciently high that the Working ?uid acts as a liquid. In such cases, the ridges 498 may be used to act as a liquid thrust bearingtohandletheforces(loads)generatedbythe?oW of theWorking?uid. FIG. 5 shoWs a detailed vieW of turbine 104. As shoWn here, the turbine has a center 558 and a periphery 558. The periphery is substantially circular, except for a plurality of cutouts567extendingtoWardsthecenter558oftheturbine 104. The cutouts 558 permit a greater quantity of ?uid to pass abouttheturbineasitrotatesintheturbinecavity280 (FIG. 2).The siZe, shape and quantity ofcutouts may be selectedto manipulatethe?oW of?uidpasttheturbine,toadjustpres suresabouttheturbineand/ortoprovidethrustbalancing across the turbine. FIG. 6, depicts a method 601 of generating poWer. The method involves steps 603-633. The steps provided are not necessarilyinorderand/orperformedaccordingtoaspeci?c timing.Themethodisdescribedinrelationtotheoperationof a thermodynamic system, such as the thermodynamic system 100and/ortheTAC 102asdescribedWithrespecttoFIGS. 1-4.Themethodinvolvesprovidingathermodynamicsystem forgeneratingpoWer(step603).Thethermodynamicsystem 100includesahousing109,analtemator108,aturbine104 and a compressor 106 (see FIGS. 1-4). The Working ?uid is compressed (step 605) in the com pressor cavity 278 by passing the Working ?uid across the compressor 106 (see, e.g., FIGS. 2-3). The Working ?uid passesacrossahigh-pressureface394andaloW-pressure face392ofthecompressor106(see,e.g.,FIGS.3-4).ApoWer output is generated (step 607) by passing the compressed Working ?uid across the turbine 104 (see, e.g., FIG. 2). TAC components, such as bearings 114,215, rotor 110 and/oraltemator108intherotorcavity112,maybecooled (step611)byselectivelyleakingaportionoftheWorking?uid past one or more seals 182 and into the rotor cavity 112 ofthe housing 109 (see, e.g., FIGS. 2-3). Thrust applied to the rotor shaft 110 is balanced (step 615) by pumping the Working ?uid as it passes across a loW pressure side 394 of the compressor 106. Preferably, the pumping reduces a pressure differential betWeen the loW pressure face 394 and a high-pressure face 396 of the com pressor 106 (see, e.g., FIGS. 2-4). Thrust may be further balancedbyprovidingcutouts567intheturbine104to manipulate ?uid ?oW therethrough. The Working ?uid may be manipulated as it?oWs through the system. The Working ?uid may be chilled (step 619) as it passesfromtheturbine104tothecompressor106.TheWork ing ?uid may be heated (step 621) as itpasses from the compressor 106 to the turbine 104. Heat exchangers, such as chiller 160, recuperator 161 and/or heater 162, may be pro vided to adjust parameters, such as temperature, of the Work ing ?uid as itpasses through the system (see, e.g., FIG. 1). The parameters of the Working ?uid may be measured (623) as the Working ?uid ?oWs through the ?uid circuit. Various devices, such as ?oW meters 150, thermometers 152, FIG. 4 shoWs the compressor 106 in greater detail. The high-pressure face 394 of the compressor 106 has a plurality ofvanes496extendingtherefrom.As shoWn,thepluralityof vanes 496 extend from the high-pressure face 394 of the compressor 106 and toWard the compressor inlet 270 (FIG. 3).Thevanes496aredepictedashavingacurvedshape20 extending from the high-pressure face 394. Preferably, the vanes 496 are con?gured to pressurize the Working ?uid and facilitatethe?oW oftheWorking?uidinamannerthatopti miZesoperationoftheTAC 102asthe?uidpassesoverthe compressor106forcompressionthereof. The compressor 106 is also depicted as having a loW pressure face 392 With a plurality of ridges 498 thereon. The ridges 489 extend radially about the loW-pressure face 392. The ridges 498 are depicted as having a linear shape extend ingfromtheloW-pressureface392toWardrotorcavity112 30 (FIG.3),butcanhaveothershapes.Preferably,theridges498 are con?gured to act as pump-out vanes for manipulating the Working ?uid as it?oWs across the compressor 106. Referring noW to FIGS. 3 and 4, the Working ?uid has a pressure(pl)asit?oWsthroughthecompressorinlet270and 35 to the compressor 106. The pressure of the Working ?uid increases to a pressure (p1) at the high-pressure face 394 of the compressor 106 as itpasses over the vanes 496 and into the compressor cavity 278. The loW-pressure face 392 of the compressor106isatapressure(p2)Whichisapproximately40 the same as the compressor inlet pressure (pl). Thepressure(p2)ofloW-pressureface392isloWerthanthe pressure(pl)ofhigh-pressureface394.A pressuredifferen tial (Aplz), therefore, exists betWeen the loW-pressure face 392andthehigh-pressureface394ofthecompressor106. 45 For example, a compressor having a diameter of 1.5 inches (3.81 cm) and a pressure of 1000 psi (6.89 MPa) at the loW-pressurefaceandapressureof2000psi(13.79MPa) at thehigh-pressurefaceduringoperationhasapressurediffer ential across the compressor that can result in axial forces 50 along the axis of the rotor shaft of up to about 1000 lbs (4448.22N). Ridges 498 are preferably used to increase pressure at the loW-pressure face 392 to balance the pressure differential Apl2acrossthecompressor106.Theseridges498actas55 pump-outvanescausingthepressureontheloW-pressureface 392 of the compressor 106 to increase. Preferably, the increased pressure on the loW-pressure face 392 decreases the pressuredifferentialAp12betWeentheloW-pressureandhigh pressure faces (392,394) ofthe compressor 106. The pressure (p1) of the high-pressure face 394 and the pressure (p2) at the loW-pressure face 392 are preferably balanced to reduce the thrust loads on the TAC 102. The dimensions of the ridges 498 and/or vanes 496 may be adjusted to manipulate ?uid ?oW and/or reduce the total 65 thrust.The manipulationofthepressuresacrossthecompres sor to reduce the pressure differential Ap 12 and reduce the US 8,397,506B1 25 60PDF Image | United States Patent Wright et a1. TURBO-ALTERNATOR-COMPRESSOR DESIGN FOR SUPERCRITICAL HIGH DENSITYWORKING FLUIDS
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