Wall Heat Fluxes in Rocket Combustion Chamber with Porous Injector Head

摘要: Wall heat fluxes in a rocket combustion chamber with porous injector head have been measured by the calorimetric method at ratio of oxidizer to fuel (ROF) 6 and pressure 80 bars. The hot tests were run on P8 test bench DLR-Lampoldshausen. wall fluxes, temperature wall, along axis every 50 mm. experimental results are characterised drop within first mm from face increase flux after flow inside has simulated using ANSYS CFX (commercial computational fluid dynamics (CFD) code). Turbulence was modelled Reynolds Averaged Navier-Stokes (RANS) equations Shear-Stress-Transport (SST) model. help different models: Eddy Dissipation Model (EDM) Extended Coherent Flame (ECFM). simulations agree data well. EDM model yields which error. quantitative disagreement numerical models is observed only region near head. employed compared each other data. gives better results. This explained more correct estimation coefficients absence empirical hydrogen high pressure.