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significant reduction in the adverse pressure gradients associated with the collision of compression waves with neighboring turbine blades. A numerical example of an entirely isentropic supersonic cascade is presented. Transonic flows of a dense gas around the leading edge of a thin airfoil with a parabolic nose had been studied by Rusak [23]. Asymptotic expansion of the velocity potential function were constructed in terms of the airfoil thickness ratio in an outer region around the airfoil and in an inner region near the nose. In [24] Brown & Argrow simulated shock tube flows with compressive wedges and circular areas. Non-classical phenomena, like expansion shocks and composite waves demonstrate significant differences from perfect gas flow fields over similar geometries. Wang & Rusak [26] provided numerical studies of transonic BZT flows past a NACA0012 airfoil at zero angle of attack (non lifting case) using the numerical code of Morren [18], and provided a classification of possible flow patterns for oncoming flow conditions such that Γ∞,Λ∞ ≈0, guided by the asymptotic theory developed in [23]. Cramer & Park in [27] considered the reflection of oblique compression waves from a two-dimensional, steady, laminar obundary layer on a flat, adiabatic plate at free-stream pressure such that dense gas effects are non-negligible. Numerical results showed a suppression of shock induced separation in supersonic Bethe-Zel'dovich-Thompson flows past sharp compression corners. Results concerning flows through realistic impulse turbine cascades had been presented by Brown [28], who solved the Euler equations closed by the Martin- Hou gas model. Operating under the proper thermodynamic conditions, a BZT working fluid can potentially weaken or eliminate shock waves. This would reduce losses due to both the wave drag from shocks as well as losses from boundary-layer separation due to shock reflections on the turbine blades. Results showed significant improvements in turbine efficiencies for BZT working fluids over conventional ORC working fluids. Kluwick in [31] discussed a new form of marginal boundary layer separation in laminar flows of dense gases using asymptotic methods: the non monotonous Mach-number variation with pressure leads to non conventional distribution of the shear stress and displacement body in boundary layers subjected to adverse pressure gradients, which contributes to delay separation. In [32] and [33] Fergason & Al., in preparation for a shock tube experiment, presented a theory to demonstrate a single-phase vapor rarefaction shock wave in the incident flow of the shock tube. The analysis predicts just a small region of initial states that may be used to unequivocally demonstrate the existence of a single-phase 23PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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