Improved prediction of heat transfer in a rocket combustor for GOX/Kerosene

The knowledge of the mechanisms influencing the heat transfer in a single element rocket combustor using GOX/Kerosene is a very important aspect when designing an experiment for this setup. Therefore much work is invested in tools capable to predict and analyze the heat transfer from the combustion chamber wall to the coolant channels. Facing the task of commonly preparing a test setup for the investigation of film cooling and transpiration cooled CMC structures, the partners of the multi-national and EU-funded project 'Aerodynamic and Thermal Load Interactions with Lightweight Advanced Materials for High Speed Flight', short ATLLAS, conducted a benchmark of their different methods to predict wall heat fluxes and to calculate the wall temperature. A "common approach" for the prediction of heat transfer in a small rocket chamber has been developed and published in the past. When more experimental data and sophisticated CFD results become available the assumptions made will be checked critically and revised. This paper summarizes conducted experimental and numerical investigations, compares the data with the "common approach" and traces back the efforts to improve prediction quality.