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44 3 Numerical methods 3.3.2 Stator and nozzle simulations The simulations were performed for a convergent-divergent nozzle and for different stator geometries. The studied geometries were 2D-geometries. In the nozzle simulations, the total enthalpy and momentum were used as the inlet boundary conditions, and the zero- gradient outlet boundary was used in the simulations since the outlet flow velocity, normal to the outlet boundary, is supersonic in the nozzle simulations. In the stator simulations, one 2D stator flow channel geometry was modelled, and the periodic boundary conditions were used in the inlet block and outlet block. Total enthalpy and momentum were used as the inlet boundary conditions, and uniform static pressure distribution was defined as the outlet boundary in the stator flow channel simulations, because the flow velocity, normal to the outlet boundary, is subsonic. The stator and nozzle blades were treated as solid walls. Structured grids were used in the modelling and the computational grids were generated to have the nondimesional wall distance y+ close to unity at the cell adjacent to the solid walls, in order to solve the boundary layer accurately. An example of a 2D convergent-divergent nozzle geometry is presented in Figure 3.8, and a 2D stator flow channel presenting the used boundary conditions and an example computational grid are presented in Figure 3.9. Figure 3.8: Example geometry and computational grid of a supersonic nozzle. 3.3.3 Rotor simulations Rotor geometries were studied by modelling one 3D rotor flow channel by using the im- plemented real gas model. The rotor blades, hub, and shroud were treated as rotating solid walls and the grids were generated to have the nondimesional wall distance y+ close to unity at the cell adjacent to the solid walls. Structured grids were used and no tip clear- ance was modelled in the rotor simulations. Periodic boundary conditions were used in the inlet and outlet blocks. An example of a structured computational grid and the bound- ary conditions used in the rotor flow channel simulations are presented in Figure 3.10. The inlet conditions of the rotor simulations were based on the area averaged results of the stator simulations and by assuming an uniform flow distribution at the rotor inlet. The velocity vectors at the inlet block were turned into the same flow angle α1 as obtained as the area averaged result in the stator flow channel simulations. It should be noted that the flow field at the stator outlet was predicted to be highly non-unifrom and thus, more accurate rotor inlet conditions would be achieved if the stator and rotor geometry wouldPDF Image | WORKING FLUID SELECTION AND DESIGN OF SMALL-SCALE WASTE HEAT RECOVERY SYSTEMS BASED ON ORGANIC RANKINE CYCLES
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