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ACCEPTED MANUSCRIPT The angle/thickness and pressure/suction modes are used to define the hub, shroud and blade profile curves for both stator and rotor blades. The ANSYS®17-Turbo Grid is employed to create the computational grid of the flow domain across the blade passages of the stator and rotor, via hexahedral mesh based on the O-H grid. ATM Optimized (Automatic Topology and Meshing) has been applied to allow the Turbo-Grid to determine an appropriate topology for the blade passage according to the blade angle, the leading edge and the trailing edge type. The grid independence studies of each turbine configuration and working fluids were carried out to ensure that the results of 3D CFD analysis are meshing independent. The computational meshes were clustered and then the simulation re-run and repeated until the mesh independent solution was reached for each turbine configuration and working fluid. Fig. 7 shows the grid independence study for each turbine configuration with R245fa as the working fluid, where the solution becomes grid-independent by the number of nodes above those listed in Table 7. While Fig. 8 shows the mesh density of the blade-to-blade passage for each turbine configuration. The 3D CFD simulations are conducted by solving RANS equations combined with the k-ω/SST (shear stress transport) turbulence model through the ANSYS®17-CFX. The k-ω/SST turbulence model has the ability to capture the turbulence closure based on automatic wall-function treatment by identifying the non-dimensional distance (y+) of the first node after the node’s wall; where the y+ is kept equal to one or less than unity as recommended in the CFX user’s manual. The transport equations of the k-ω turbulence model used to calculate the turbulent kinetic energy and the specific dissipation rate are as follows: ∂(ρk)+ ∂ (ρkui)= ∂ (Γ ∂k)+G ‒Y +S (20) ∂t∂xi ∂xjk∂xjkkK ∂(ρω)+ ∂ (ρωui)= ∂ (Γ ∂ω)+G ‒Y +S (21) ∂t∂xi ∂xjk∂xjωωω where Gk and G represent the generation of turbulent kinetic energy and its dissipation rate; Yk and Y represent the fluctuating dilation in compressible turbulence; Sk and S are the source terms of the k- turbulence model. A mixing plane interface was applied at the turbine stage interface (i.e. stator and rotor) to provide the communication through the stationary and rotating domain of the blade rows. The GGI (i.e. Generalised Grid Interface) feature was used with steady state flow and stage analysis. All CFD simulations were carried out under steady state flow condition with convergence criterion of 10-5 for all residuals (RMS) values and a time scale of 0.5/Ω as recommended in the CFX user’s manual. The inlet’s total pressure and temperature were fixed at the turbine stage inlet while the static pressure was specified at the turbine stage outlet (i.e. rotor outlet); 16PDF Image | turbine configuration for low-power organic Rankine cycle
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