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P. Colonna, S. Rebay, J. Harinck and A. Guardone the state-of-the-art Span-Wagner (SW) EoS on the predicted aerodynamic performance parameters and flow features of an existing ORC turbine blade that operates, at least partly, in a thermodynamic region where the ideal gas assumption does not hold. The fluid dynamic results are very similar for the SW and PRSV EoS. The PIG EoS, on the other hand, shows large relative differences in almost all parameters, when compared to the accurate SW EoS. As expected, the PIG EoS underpredicts the density in the initial portion of the expansion process by more than 30%. The Mach number distribution along the blade surface appears surprisingly similar for all mentioned EoS models. This is due to the fact that, although the first portion of the expansion process occurs in the more nonideal gas thermodynamic region, the Mach number here is low, so that the initial high nonideality has little effect on the absolute value of the Mach number. Moreover, the flow is chocked and so the Mach number is equal to unity at the nozzle throat. Since the distance from the leading edge (where M = 0) to the throat is small, more or less the same profiles are observed. The final portion of the expansion process occurs at lower pressure states that are much closer to the ideal gas region, thus limiting the effect on the, at this point, high absolute Mach number. The effect of the initial high nonideality does become apparent in the initial portion of the distribution of the relative difference in the Mach number among the PIG and the real gas models (SW and PRSV), where it is as high as 10%. Nonetheless, this is small compared to the relative difference in sound speed, which is at maximum 48%. This results from the fact that the incorrectly higher sound speed predicted by the PIG EoS is compensated by a velocity magnitude that is similarly higher. As the process evolves toward lower pressure (close to ideal gas) states and the relative difference in sound speed among the PIG and the real gas models decreases, the relative difference in velocity magnitude also decreases, thus limiting the relative difference in the Mach number. Very large differences in densities among the PIG and the real gas models (SW and PRSV) can be observed in the initial portion of the expansion. The large initial difference can be expected, since pressure and temperature are the prescribed variables at inflow and outflow and density depends on the EoS model. For the latter reason, the distribution of the pressure coefficient shows only small differences among EoS models and its trend is similar to the one of the Mach number. In part-load conditions, the PIG EoS predicts stronger shock waves, shown by a 6% higher total pressure loss coefficient and the less uniform distributions of Mach number and flow angle along the outflow boundary. The application of the PIG model results in an average stator outflow angle deviation of 1.5◦ with respect to the real-gasa models, which may lead to a less-than-optimal design of the rotor blades. The predicted mass flow is 6.8% lower for the PIG EoS and 0.4% higher for the PRSV EoS, both compared to the one predicted by the accurate SW EoS. If this ORC stator blade were designed using the PIG EoS, the large error in the predicted relation of mass flow with respect to pressure ratio would also affect the operation of the other components in the ORC cycle, possibly leading to suboptimal cycle performance. 16PDF Image | REAL-GAS EFFECTS IN ORC TURBINE FLOW SIMULATIONS
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