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List of Figures Figure 1: Amagat diagrams for a van der Waals BZT gas with γ=1.0125 (a) and for the heavy fluorocarbon PP10 modeled through the Martin-Hou equation of state (b). The shaded region represents the inversion zone........................................................................36 Figure 2: Location of the operation points in the p − v diagram. ........................................ 48 Figure 3: Fundamental derivative versus pressure along selected isentropes. ....................49 Figure 4: Aerodynamic coefficients versus free-stream fundamental derivative for flow at ............................................................................................................................................. 54 Figure 5: Pressure coefficient contours and Γ = 0 contours for operating conditions.........54 Figure 6: Wall distributions of the Mach number, pressure coefficient, fundamental derivative .............................................................................................................................55 Figure 7: Pressure coefficient contours and Γ = 0 contours for operating conditions.........56 Figure 8: Wall distributions of the Mach number, pressure coefficient, fundamental derivative .............................................................................................................................57 Figure 9: Pressure coefficient contours and Γ = 0 contours for operating conditions.........58 Figure 10: Wall distributions of the Mach number, pressure coefficient, fundamental derivative .............................................................................................................................59 Figure 11: Turbulent flow over the NACA0012 airfoil, M∞ = 0.85, α = 1°, Re = 9 × 106. Pressure coefficient contours and streamlines (left) and wall pressure coefficient (right) for a perfect gas flow (a,b) and for PP10 at operating conditions p∞/pc = 1.01, ρ∞/ρc = 0.676 (c,d), p∞/pc = 1.08, ρ∞/ρc = 0.850 (e,f), p∞/pc = 1.17, ρ∞/ρc = 1.11 (g,h)..............................62 Figure 12: Aerodynamic coefficients versus free-stream fundamental derivative for turbulent ............................................................................................................................... 63 Figure 13: Skin friction for a perfect gas flow and dense gas flows at different operating.64 Figure 14: Isobares for a perfect gas (a), steam (b), and PP10 (c).V KI LS-59 cascade. .... 66 Figure 15: Cascade efficiency versus inlet Fundamental Derivative.Le ft: SC11 cascade; 67 Figure 16: Mach distributions at the wall. VKI LS-59 cascade...........................................67 Figure 17: Pressure distributions at the wall. VKI LS-59 cascade. ..................................... 68 Figure 18: Γ distributions at the wall. VKI LS-59 cascade. ................................................68 13PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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