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FIGURE 3-18: SNL SUPERCRITICAL CO2 DATA ACQUISITION AND CONTROL SYSTEM DISPLAYING THE T-S AND T-D STATE DIAGRAMS. THE IMAGE ON THE LOWER LEFT SHOWS THE T-S DIAGRAM AND THAT THE COMPRESSOR INLET IS VERY NEAR THE CRITICAL POINT. THE DISPLAY ON THE RIGHT SHOWS A SIMILAR PLOT BUT SHOWS THE TEMPERATURE-DENSITY (T-D) DIAGRAM. THE BLACK LINE IS THE SATURATION CURVE..................................................................................................... 39 FIGURE 4-1: RPCSIM (REACTOR POWER AND CONTROL SIMULATOR) FOR THE SANDIA SUPERCRITICAL COMPRESSION LOOP. THIS FIGURE SHOWS THE SIMULINK MODULES THAT ARE USED TO MODEL THE COMPRESSION LOOP. THE MODEL USES THE NIST REFPROP EQUATION OF STATE FOR SUPERCRITICAL CO2 AND IT USES AND ENTHALPY BASED NON-LINEAR SOLUTION TECHNIQUE TO MODEL THE FULL DYNAMIC SYSTEM, INCLUDING STARTUP......................................................... 40 FIGURE 4-2: DYNAMIC SIMULATION RESULTS ILLUSTRATING THE STARTUP OF THE COMPRESSION LOOP. THE TOP FIGURE SHOWS THE POWER ADDED TO THE GAS (YELLOW) DUE TO THE SPIN UP OF THE COMPRESSOR, AND THE BLUE CURVE SHOWS THE HEATREMOVEDBYTHEGASCHILLER. THESECONDPLOTSHOWSTHESPINUPOFTHECOMPRESSOR(BLUE)WHILETHE LOWER CURVES SHOW THE MASS FLOW RATE. THE THIRD SET OF CURVES SHOW THE COMPRESSOR INLET TEMPERATURE (YELLOW) AND THE COMPRESSOR OUTLET TEMPERATURE (MAGENTA). THE BOTTOM PLOT SHOWS THE COMPRESSOR INLET PRESSURE WHICH REMAINS NEARLY CONSTANT REGARDLESS OF THE SHAFT SPEED, AND THE COMPRESSOR OUTLET PRESSURE. ........................................................................................................................................................................... 42 FIGURE 5-1: TEMPERATURE ENTROPY (T-S) PLOT SHOWING THE COMPRESSOR INLET STATE POINT LOCATIONS FROM SELECTED SPIN TESTS. .......................................................................................................................................................................... 45 FIGURE 5-2: TEMPERATURE ENTROPY DIAGRAM FOR CO2 NEAR THE CRITICAL POINT. THE GREEN CURVES INDICATE THE T-S PATH FOR CO2 FLOW IN THE GAS CHILLER, IN THE COMPRESSOR AND DURING HEATING IN EITHER THE RECUPERATOR OR A HEATER. THE RED LINES SHOW THE RANGE OF COMPRESSOR INLET CONDITIONS THAT WE INTEND TO OPERATE THE LOOP AT. NOTETHATTHEYROUGHLYFOLLOWTHELINESONCONSTANTDENSITYANDVARYFROMALOWDENSITYOF0.15 KG/LITER TO A HIGH DENSITY OF 0.80 KG/M3 OVER A TEMPERATURE RANGE FROM 290 K TO 318 K. THE BLUE DOTTED LINE SHOWS THE PSEUDO-CRITICAL POINTS WHERE LARGE PEAKS IN THE HEAT CAPACITY AND VISCOSITY ARE OBSERVED........ 46 FIGURE 5-3: IMAGE FROM THE SANDIA S-CO2 COMPRESSION LOOP CONTROL SYSTEM SHOWING THE LOCATION OF THE STATE POINTS ON THE T-S DIAGRAM. RED AND GREEN POINTS ARE COMPRESSOR INLET AND OUTLET CONDITIONS (RESPECTIVELY) AND THE BLUE POINTS ARE THE T-S CONDITIONS AFTER THE FLOW CONTROL VALVE WHICH IS AT THE INLET TO THE GAS CHILLER............................................................................................................................................................................... 47 FIGURE 5-4: RECORDED TEMPERATURES IN TEST CBC_081202_0819 SHOWING THE REDUCTION IN TEMPERATURE TO BELOW THE CRITICAL POINT AT 866 S INTO THE TEST. T400 IS THE COMPRESSOR INLET TEMPERATURE AND T500 IS THE OUTLET. 48 FIGURE 5-5. THE BEHAVIOR OF THE COMPRESSION LOOP WHEN THE COMPRESSOR INLET TEMPERATURE AND PRESSURE FALL BELOW THE CRITICAL POINT IS ILLUSTRATED IN THE ABOVE FIGURE. NOTE THAT THE MEASURED FLOW RATE IS MULTIPLIED BY A FACTOR OF 10.............................................................................................................................................................. 48 FIGURE 5-6. THE FIGURE SHOWS AN EXPANDED VIEW OF THE DENSITY AND FLOW OSCILLATIONS THAT WERE OBSERVED WHILE OPERATING BELOW THE CRITICAL POINT. NOTICE THE OUT-OF-PHASE RELATIONSHIP BETWEEN MEASURED MASS FLOW RATE AND DENSITY.............................................................................................................................................................. 49 FIGURE 5-7: MEASURED MOTOR POWER, MASS FLOW RATE, AND SHAFT SPEED THROUGH THE SUPERCRITICAL CO2 COMPRESSOR DRIVEN. PEAK SHAFT SPEED IN THIS TEST WAS 65,000 RPM, THE FLOW RATE 5.25 LB/S AND THE MOTOR POWER WAS 53 KW. ..................................................................................................................................................................................... 51 FIGURE 5-8: MEASURE PRESSURE RISE FOR THE STAIR STEPPED INCREASE IN SHAFT SPEED. P500 IS THE COMPRESSOR OUTLET PRESSURE, P400 IS THE COMPRESSOR INLET PRESSURE, AND P100 IS THE STATIC PRESSURE AT THE TIP OF THE COMPRESSOR BLADE. PDRAIN IS THE ROTOR CAVITY PRESSURE THAT WAS REDUCED TO REDUCE WINDAGE LOSSES................................ 52 FIGURE 5-9: MEASURED PRESSURE (PSIA) AT THE MAIN COMPRESSOR INLET (P400) AND OUTLET (P500) AS A FUNCTION TIME. P100 IS THE STATIC PRESSURE AT THE TIP OF THE COMPRESSOR WHEEL. PDRAIN IS THE ROTOR CAVITY PRESSURE WHICH WASREDUCEDTOLOWERWINDAGELOSSESANDTOCOOLTHEBEARINGS. THESHAFTSPEEDISALSOSHOWN..................55 FIGURE 5-10: MEASURED MASS FLOW RATE AND LABYRINTH SEAL LEAKAGE FLOW RATE (LB/S) AS A FUNCTION OF TIME. AT ~12335 S THE FLOW CONTROL VALVE WAS CLOSED IN A SERIES OF STEPS RESULTING IN A DECREASE IN FLOW FROM 8.7 LB/S TO 3.6 LB/S. ......................................................................................................................................................................... 56 FIGURE 5-11: COMPARISON OF THE PREDICTED AND MEASURED FLOW PERFORMANCE FOR THE MAIN COMPRESSOR IN THE SNL SUPERCRITICAL CO2 TEST LOOPS. THE PLOT SHOWS THE CORRECTED ENTHALPY CHANGE AS A FUNCTION OF CORRECTED MASS FLOW RATE FOR PARAMETRIC VARIATIONS IN CORRECTED SPEED. THIS PERFORMANCE MAP WAS MADE AT COMPRESSOR INLET TEMPERATURE AND PRESSURE CONDITIONS THAT WERE VERY NEAR THE CRITICAL POINT OF 304.1 K AND 7377 KPA. DURING THESE TESTS THE COMPRESSOR INLET CONDITIONS VARIED FROM 304.3 – 307 K AND 7700-8139 KPA. .................................................................................................................................................................................... 57 FIGURE 5-12: COMPARISON OF THE PREDICTED AND MEASURED COMPRESSOR EFFICIENCY FOR THE MAIN COMPRESSOR IN THE SNL SUPERCRITICAL CO2 TEST LOOP. THE PLOT SHOWS THE COMPRESSOR EFFICIENCY (T-S) A FUNCTION OF CORRECTED 7PDF Image | Operation and Analysis of a Supercritical CO2 Brayton Cycle
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