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Mathematics 2020, 9, 50 13 of 30 Figure 12. Mesh of the passage with 1.0 × 106 elements. Figure 13. Mesh independence study using ANSYS TurboGrid. Figure 13. Mesh independence study using ANSYS TurboGrid. 4.2. Turbulence Model, Physical Domain, Boundary Conditions, and Governing Equations During the past two decades, two main turbulence models have been developed: k − ε model, which is based on the turbulence dissipation rate ε, and k − ω model, which is based on the specific dissipation rate ω. Fajardo [60] indicated that k − ω is more accurate than k − ε in computing the near-wall layers. However, k − ε converges faster and is robust with real gas applications [36]. Menter [61] developed less complex and less computationally expensive model called shear stress transport (SST) model. The SST model applies the k − ω model to capture the near-wall region accurately and switches to the k − ε model in the free-stream to avoid the sensitivity of k − ω to the effects of free- stream turbulence. Menter’s predicted results using the SST model are in good agreement with the experimental data. Therefore, k − ω SST is applied in the current analysis for both the design point and off-design analyses. To reduce computational time, a single flow passage for the rotor and stator is sim- ulated and rotational periodicity is applied by setting an appropriate pitch ratio at the interface between the stator and rotor. Different meshing is required because of the different components considered in the simulation. Therefore, the position of the grid nodes in one domain may not match those in the other domains. The general grid interface is applied to avoid such non-matching interface. Domain interfaces are required because a change in reference frame between stationary (stator) and rotating (rotor) domains occurs. ANSYS CFX has two main interfaces, namely, mixing plane and frozen rotor. The main difference between the two interfaces is that the mixing plane applies the average qualities on the interface for upstream and downstream components; therefore, it is applied in the current study. Figure 14 shows the modelled components with the corresponding fluid domains.PDF Image | Generation of 3D Turbine Blades for Automotive ORC
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