超音速矢量喷嘴燃烧.pptx

Nozzle Combustion and Cooling w/ STAR-CCM+ Vector Space;Geometry & Mesh Problem Definition Multi-Species Approach Gas Phase Reacting Flow Lagrangian Droplet Injection + Gas Phase Reactions Lagrangian Droplet Injection + Fluid Film + Gas Phase Reactions Comparison of Results Comparison of Computational Cost;Nozzle geometry provided by Vector Space Fluid volume extracted using STAR-CCM+;Coarse Polyhedral Grid with Prism Layers (use assumed wall functions in BL) 133K Cells ;Chamber Pressure: 12.4 bar. Fuel: 0.309 kg/s Propyle (C3H6) injected at 225K in 8e-5m diameter droplets Oxidizer: 0.804 kg/s LOX injected at 90K in 1e-4m diameter droplets Fuel Film: 0.015 kg/s Propyle liquid attached to the solid wall O/F Ratio = 2.6 Want to include the effects of: Radiation from the nozzle to the external Evaporation of the two droplet species and fluid film into the gas phase Gas phase reacting flow Vector Space provided NASA-CEA output for this condition for purposes of comparison.;Desired Problem Description;Use the NASA CEA output at the end of combustion and assuming the evaporation is complete and reactions are frozen. Solve one set of discretized N-S equations for all species on the polyhedral grid Initial conditions found from 1D isentropic flow solution (calculated w/ a java macro). Active Species: CO, CO2, H2O, OH, H2, H, O2, O Fuel not considered in this case as it has all been combusted into other species NASA 5 coeff polynomials for Cp of each species Peng-Robinson real gas eqn. of state Other species properties constant Mixture properties calculated as mass-weighted averages of species properties Solid conduction w/ anisotropic thermal conductivity Surface-to-Surface gray body radiation to background (no participating gas radiation).;Initial Conditions;Boundary Conditions;Multi-Species Convergence History;Multi Species Results;Multi Species Results;Use the same approach as multi-species case, but include the gas phase reactions. Active Species: C3H6, CO, CO2, H2O, O