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Wang et al. 9 These tables are integrated into an RGP file by using in-house developed code, and the RGP file is inte- grated into the software of ANSYS CFX to complete the CFD solution process. In this study, nine tables are adopted to describe the thermophysical proper- ties, shown as follows hðP, TÞ, cðP, TÞ, vðP, TÞ, CVðP, TÞ, CPðP, TÞ, ð@P=@vÞT ðP, TÞ, sðP, TÞ, ðP, TÞ, kðP, TÞ ð23Þ Effects of gas model. Table 3 shows the performance comparison of stage 1 by using real gas property and ideal gas model. The relative differences of the mass flow is 0.39%, relative differences of output power is 9.36%, which is much higher. The isentropic efficiency is determined by the ratio of actual enthalpy drop and isentropic enthalpy drop. When the ideal gas model is employed, the deviations for the isentropic enthalpy drop and actual enthalpy drop in similar proportion. In Table 3, the relative differences for isentropic drop of enthalpy is -7.36%, the relative dif- ferences for actual drop of enthalpy, which can be derived from mass flow and output power, is 9%. Thus, the relative difference for total to total efficiency is 1.7%, which is small. Same results can also be observed in Zhang et al.30 Figures 9 and 10 depict the streamlines on the sur- face of stator and rotor obtained by using real gas property and ideal gas model. It can be found that the distribution of streamlines obtained by the two models is nearly the same. The shape and location of horseshoe vortex and the vortex near throat of stator is almost identical. In the rotor, the topological structure of streamline on the suction and pressure surface of blade, hub, and shroud are also nearly the same. These results illustrate that the ideal gas model has little effect on the flow pattern under super- critical condition. Figure 11 depicts the distribution of static entropy, Mach number, and pressure in the rotor. It can also be found that static entropy, Mach number, and pres- sure in the stator obtained by the two models are also nearly the same. As shown in Figure 12, the distribu- tion of inlet-to-exit total pressure ratio, inlet-to-exit Mach number at outlet of rotor are also similar, while higher entropy and lower inlet-to-exit total tem- perature ratio are obtained when ideal gas model is adopted. To provide further explanation, comparison of thermodynamic parameters between real gas prop- erty and ideal gas model is shown in Figure 13. Figure 11. Distribution of static entropy, Mach number, and pressure in the rotor: (a) sketch of observe location; (b) static entropy distribution; (c) Mach number distribution; (d) pressure distribution.PDF Image | radial turbine supercritical compressed air energy storage
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