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Then, the previous shape optimization has been reconsidered for viscous transonic flows of dense gases over airfoils. Moreover, computational costs related to the great number of evaluations of the objective function by means of the Navier-Stokes solver have been substantially reduced by using a properly calibrated artificial neural network to interpolate the response surface. When solved for viscous flow, the drag minimization problem of a symmetric airfoil with fixed thickness-to-chord ratio yields indeed shock-free shapes for an extended range of the freestream Mach number. However, the problems generated by considering the viscous performances of airfoils produced by inviscid computations are completely overcome by including viscous effects into the optimization process, which provides an airfoil shape whose performance is far superior to the baseline over the whole range of Mach numbers considered for the study. The multi-point performance optimization for a lifting airfoil in subcritical and supercritical flow conditions has allowed determining an airfoil shape that provides an overall improvement of the lift coefficient while preserving the high lift-to-drag ratio typical from BZT flows. Once more, the results show the importance of taking fully into account viscous effects during the optimization process in order obtain good performance over a large operation range. The overcost related to evaluations of the fitness function via a Navier-Stokes solver is completely justified by performance improvements offered by the optimized airfoils, and could be further alleviated by means of parallel computing. Moreover, significant improvement may be expected from the use of hybrid optimization algorithms, combining the flexibility of genetic strategies with the accuracy and efficiency of gradient-based methods. Thirdly, shape optimization for flows of perfect and dense gases in turbine cascades has been achieved by means of a multi-objective genetic algorithm. For perfect gas flows, shape optimization allows efficiency improvements of about 3% over the baseline configuration. For dense gas flows, proper optimization starting from the same baseline geometry leads to efficiency gains up to 7%. Multipoint optimization allows improving performance over a large range of thermodynamic operating conditions. For the high cascade pressure ratio considered in this study, BZT effects play a minor role in efficiency improvement. The use of properly designed turbine cascades working with somewhat lower pressure ratios could allow higher efficiency improvements due to BZT effects, opening the door to the development of BZT turbines for Organic Rankine Cycles. 118PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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