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Wang et al. 17 Figure 22. Continued. of tip clearance height on the total-to-total efficiency tt of the four stages are investigated. The tip clear- ance height, which is shown in Figure 3(a), is defined by the percentage of rotor blade height at outlet. And it keeps constant from the inlet to the outlet of the rotor. The total-to-total efficiency of radial turbines is defined as tt1⁄4h0h2 ð26Þ h0 h2,S where h2 is the isentropic total enthalpy at observa- tion surface; h2,S represents the isentropic total enthalpy at outlet of rotors. As shown in Figure 20, total-to-total efficiency tt for all of stages decreased with the increase of the tip clearance height. However, when the tip clearance height increases from 0% to 4%, the total-to-total efficiencies of stage 1, stage 2, stage 3, and stage 4 are reduced by 3.17%, 5.2%, 3.75%, and 5.78%, respectively. By comparing the parameters in Table 1, it can be found that stages 2 and 4, which have higher value of , present higher efficiency reduction compared to that of stages 1 and 3. The entropy contour corresponding to the flow loss in the rotor of the four stages is shown in Figure 21. For all of the stages, the high entropy region moves to the pressure surface of the adjacent blade with the increase of the tip clearance height, the influence range is also increased, and the total-to-total isen- tropic efficiency tt is thus decreased. For the rotor of stages 2 and 4, the influence range of high entropy region (marked with dotted lines) increases more obviously. That is why stages 2 and 4 present higher efficiency reduction. Pressure distribution at blade surface of rotor near tip clearance (90% span) is shown in Figure 22. For the rotors of stages 2 and 4, the pressure fluctuation on the suction surface at the leading edge of the blade is more obvious. This is because the blade with higher value of also has higher blade height difference between inlet and outlet of rotor, and the proportion of tip clearance in the blade inlet height is thus increased. Therefore, leakage flow at leading edge of rotor is increased, and more serious pressure fluctu- ation is observed. Conclusion The present study firstly conducted a numerical simu- lation of a multistage radial turbine of CAES. Influence of ideal gas model on the radial turbinePDF Image | radial turbine supercritical compressed air energy storage
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