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Wang et al. 7 Figure 7 depicts the geometry of the NASA compact inflow turbine.27 Table 2 shows the overall performance comparison for NASA radial turbine.The relative errors for mass flow, total to total efficiency, and output power are - 0.36%, 2.70%, and þ2.64% respectively, which are within engineering permissible error range. These errors may be attributed to the adoption of circumfer- ential average treatment at rotor–stator interface, adiabatic wall, and smooth channel in the CFD model. Comparison of outlet parameter distributions are shown in Figure 8. It can be found that total-to-total efficiency, total pressure ratio, total temperature ratio, and flow angle obtained by numerical simulation pre- sent higher errors at 30–70% span location. This is mainly due to the exist of rotor back gap in the experi- ment.23 Overall, the calculated distrbutions agree well with the experiemtal data. Effects of gas model on the performance and flow pattern of radial turbine The radial turbine of stage 1 is operated under the supercritical condition, and it is still not clear that the solution precision of the supercritical gas flow using ideal gas model. To provide reference for the analysis and design of radial turbine with similar condition, the effects of gas model on the performance and the flow pattern of radial turbine is investigated in the present study. Description of the gas models Ideal gas model. For the ideal gas model in ANSYS CFX, density is calculated from the ideal gas law and CP is considered as a function of temperature. The thermodynamic parameters can be calculated as follows 1⁄4 wPabs ð17Þ R0T Table 3. Performance comparison of stage 1 using real gas property and ideal gas model. Real gas Ideal gas property model Relative differences 0.39% 1.70% 9.36% 7.36% Mass flow (kg/s) Total-to-total efficiency (%) Output power (kW) Isentropic drop of enthalpy (kJ/kg) 5.01 89.26 425.41 95.13 4.99 87.74 385.59 88.13 Figure 8. Comparison of the parameters distribution at outlet of rotor for NASA turbine: (a) total-to-total efficiency; (b) total pressure ratio; (c) total temeperature ratio; (d) flow angle a.PDF Image | radial turbine supercritical compressed air energy storage
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