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92 1D design CFD Geometry 1 CFD Geometry 2 CFD Geometry 3 6 Radial turbine design for a micro-ORC test setup Case pin pin/pout [bar] [-] 0.40 6.2 0.42 8.6 0.38 7.9 0.37 7.0 ∆Trot [o C] 12.7 19.4 18.1 16.2 cin Mac [m/s] [-] 289.7 2.18 240.4 1.81 255.9 1.93 253.8 1.91 win [m/s] 107.4 M aw ηst−st [-] -ηrel, [%] 0.81 0 Table 6.7: Rotor simulation results 98.4 0.74 110.7 0.83 114.16 0.86 + 4.1 + 1.4 + 1.6 compared to the prediction of 1D turbine design. It should be noted that based on the simulated results, the rotor inlet velocity is lower at the rotor inlet when compared to the results obtained in the stator simulations as well as in the rotor 1D design. This has an effect on the predicted rotor flow field mainly due to the slight differences in flow angle and velocity triangle at the rotor inlet, when compared to 1D design and to the results obtained in the stator simulations. In addition, as presented in the stator simulations the flow angle distribution is non-uniform at the rotor inlet unlike the one that was used in the rotor simulations. The results indicate that the relative Mach number and relative ve- locity at the rotor inlet predicted in the CFD simulations agrees well with the 1D turbine design. A slightly higher rotor static to static state efficiency is predicted by the CFD- simulations when compared to the efficiency prediction used in the 1D turbine design. The CFD simulations do not take into account the rotor tip clearance loss or the losses re- lated to the shock waves from the stator trailing edge causing flow separation at the rotor blades(Rinaldi et al., 2013) and thus, the rotor efficiency is estimated to be slightly lower than the one predicted in the CFD simulations. The pressure distribution in the mean line of the rotor blade pressure and suction side are presented in Figure 6.16a, Figure 6.16b and Figure 6.16c. Based on the results, the location of the flow separation on the blade pressure and suction side can be observed as the increase in the static pressure in Figure 6.16a, Figure 6.16b and Figure 6.16c. An example of the simulated rotor static pressure, static temperature, and velocity contours of rotor Geometry 3 is presented in Figure 6.17a, Figure 6.17b and Figure 6.17c. Based on the simulated contours, a flow separation occurs at both the pressure side of the blade near the rotor inlet and especially at the blade suction side. The flow separation in the rotor flow channel can be clearly observed in Figure 6.17b as a region of higher temperature and in Figure 6.17c as a region of low flow velocity especially at the suction side of the blade. According to Rohlik (1975), the flow separation on the blade suction side can be prevented by increasing the number of blades and by optimizing the angle of the relative velocity. The flow separation on the pressure side of the rotor blade is estimated to be caused by the slightly incorrect flow velocity and absolute flow angle at the rotor inlet in the simulations, and thus, the relative flow angle differs from the 1D design as well. Based on the obtained results, it is recommended to make simulations in which the stator and rotor are coupled together to study the rotor inlet conditions in more detail. In addition,PDF Image | WORKING FLUID SELECTION AND DESIGN OF SMALL-SCALE WASTE HEAT RECOVERY SYSTEMS BASED ON ORGANIC RANKINE CYCLES
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