The design phase of a rocket combustion chamber relies on the prediction of the wall heat fluxes, in order to optimize the components to prevent thermal damage. Based on the experimental data of a subscale single-injector combustion chamber at elevated pressure, this work thoroughly investigates the validity of a hybrid Reynolds–Averaged Navier–Stokes/Large Eddy Simulation turbulence model (namely, Improved Delayed Detached Eddy Simulation [IDDES]) combined with efficient flamelet tables. The generation of non-adiabatic flamelets is hereby optimized compared with previous studies. The effects of chemistry and enthalpy losses are first investigated on a simplified laminar test case. Then, the influence of the grid resolution on the wall thermal loads of the single-injector combustion chamber is discussed in the context of IDDES. The use of coarser meshes increases the turbulent content of the core flow, leading to an enhanced thermal load in the rear part of the chamber. Nonetheless, all investigated meshes yield a very good agreement with the experimental data, confirming the robustness of the IDDES/non-adiabatic chemistry solver. The result is confirmed by a preliminary simulation of the same combustion chamber featuring film cooling. The IDDES/non-adiabatic flamelet model is therefore recommended as a valid alternative to the widely used wall-stress-modeled large-eddy simulation.
Delayed Detached Eddy Simulations with Tabulated Chemistry for Thermal Loads Predictions
Journal of Propulsion and Power ; 37 , 1 ; 29-46
2020-10-22
18 pages
Article (Journal)
Electronic Resource
English
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