ADVANCED MICROTURBINE SYSTEMS Final Report for Tasks 1 Through 4 and Task 6

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ADVANCED MICROTURBINE SYSTEMS Final Report for Tasks 1 Through 4 and Task 6 ( advanced-microturbine-systems-final-report-tasks-1-through-4 )

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Figure 2.2.10 Impedance at various flow rates (normalized by characteristic impedance) In order to simulate the actual engine operating temperature and pressure, the engine flow rates were scaled on the Mach number at combustor plenum. For the 70% power case the engine operating flow rate was 4.33 lb/s which scaled to 2.0 lb/s at experimental ambient pressure and temperature conditions. The 100% power case has a flow rate of 4.98 lb/s which scaled to 2.3 lb/s. Figure 2.2.10 shows the impedance calculated for mass flow rates of 2.0 and 2.3 lb/s. This plot represents normalized impedance in which 0 dB is equal to the characteristic impedance (ρc). Therefore, any value above 0 dB represented higher impedance in which more of the acoustic energy was reflected than transmitted (more closed) at the impedance boundary. Large impedance, representing an acoustically “closed” boundary, existed near 250Hz, 450Hz, 690Hz, and higher frequencies. The impedance data was then incorporated successfully into the models for acoustic stability analysis. At 100-percent power and uniform fueling of each zone, a system instability would likely exist near 480 Hz. To mitigate the risk, the fuel nozzle design was modified to allow the increase of the fuel convective length between the fuel injection point and the flame by 2 inches. As shown in Fig. 2.2.11, calculations showed that the instability was eliminated as indicated by the fact that the blue line goes below the green threshold line when convection length is increased to 4 inches. 56

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