Wall Heat Fluxes in Rocket Combustion Chamber with Porous Injector Head

Kurzfassung

Wall heat fluxes in a rocket combustion chamber with a porous injector head are measured by the calorimetric method at the ratio of oxidizer to fuel of 6 and pressure of 80 bars. The flow inside the combustion chamber is simulated using the commercial CFD code ANSYS CFX. Turbulence is modelled by the Favre averaged Navier-Stokes equations and the Shear-Stress-Transport model. The turbulent combustion of propellants is modelled using different models: the Eddy Dissipation Model and the Extended Coherent Flame Model. The results obtained with the different models are compared. The numerical results agree with the experimental results well.

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