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2 Proc IMechE Part A: J Power and Energy 0(0) three-dimensional viscous solver, and found that the secondary flow was not only one factor influencing the wake flow pattern. Dai and Chen8 analyzed the inside flow of radial micro-gas turbine rotors and revealed that tip leakage flow and corner vortex devel- oped and mixed with the main flow through the passage. Numerous factors, such as geometry and operating condition, also have great effect on the flow structures of the radial turbine. Simpson9 compared the loss gen- eration between radial turbines with vaned stators and vaneless volutes under the same operating conditions. Vaneless turbine stators incur lower losses than the corresponding vaned stators, but deliver a higher level of uniformity in the rotor inlet pressure field. Binder et al.10 analyzed the effects of variable geom- etry on radial turbines and determined that the geo- metric configuration of the stator selected to reach a specific value of the reduced section influences the efficiency of the stage. He et al.11 investigated the backface clearance flow in deeply scalloped radial tur- bines and observed that the increase in the clearance height decreases the heat transfer coefficient caused by the impingement of the scraping flow, but increases the leakage loss. Li et al.12 conducted a numerical investigation of the three-dimensional flows in a rotor of a radial turbine and observed that the inter- action and mixing between passage vortex and tip leakage vortex was the major factor influencing flow loss formation under the design conditions. However, flow separation and backflow of the mean flow occur- ring at the leading edge caused the majority of flow loss under the off-design conditions. For a microra- dial inflow turbine,13 the flow loss in rotors passage is mainly caused by stagnation of the air flow near the inlet of the impeller and boundary layer friction loss and the loss of wake vortex near the trailing edge of the impeller. Tip clearance is also one of the key factors affecting the flow field, energy transfer, work capacity, and effi- ciency of radial turbine. Amedick and Simon14 simulate the internal flow in a radial turbine rotor. Their results illustrated that the wake and nonuniform flow at outlet of the rotor not only affected by the accumulation of the low kinetic energy fluid, but also influenced by the tip clearance leakage flow, which Deng et al.15 investigated the effects of rotor blade tip clearance on total aerodynamic performance in a radial inflow turbine, and reveal that radial clear- ance increases at the rotor exit have about 8.3 times the effect on stage efficiency. In the present study, the supercritical air is employed to reduce site area and increase the energy density of CAES system,16 so the compressed air in the multistage radial turbine expands from supercrit- ical to atmospheric conditions to obtain higher output power, which differs from the ordinary operating con- dition of radial turbines (Figure 1).16–23 In addition, radial turbines, which are shrouded and unshrouded Figure 1. Total pressure and temperature at the inlet of radial turbine. rotors with different blade profile, are all included in the multistage radial inflow turbine to meet the requirement of operation condition, thus it is difficult for the engineers to determine the stage that has higher flow loss to conduct performance improve- ment. Although some studies24 has been conducted on the aerodynamic performance and internal flow patterns of multistage radial inflow turbine, the effects of supercritical condition and geometric parameters on the aerodynamic performance and flow character- istic of multistage radial turbine in CAES system is also still not revealed. In the present study, influence of ideal gas model on the aerodynamic performance and internal flow structure of supercritical radial turbine is analyzed. Effects of tip clearance on the four radial inflow turbines are also revealed. These results above will provide a reference for the further development of high-efficiency radial turbines in CAES. Description of the multistage turbo-expanders The scheme of the multistage radial-turbine system adopted in the CAES is depicted in Figure 2. Stages 1 and 2 are installed on a same rotational axis, whereas stages 3 and 4 are installed on another. These four radial turbines are integrated into one multistage radial turbine through a gear box to gen- erate work output together. Each radial turbine is connected through a pipe, and a preheater is also included to increase inlet temperature of radial tur- bine. A collection chamber is adopted at inlet of radial turbine to ensure uniformity of the air flow. The inlet total pressure and rotational speed for each stage is shown in Table 1. The sketch of the radial inflow rotor adopted in the present work is shown in Figure 3. The detailed geo- metric parameters are shown in Table 1. A new geom- etry parameter , which is defined as the ratio of blade height difference (lout lin) to rotor axial length lAxial, is adopted in the present study. This parameter is used to evaluate the variation rate of blade height fromPDF Image | radial turbine supercritical compressed air energy storage
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