Internal Application of Ultra-Fast Temperature Sensitive Paint to Hydrogen Combustion Flow

The paper will discuss an experimental approach to determine wall surface heat flux in a hydrogen combustion chamber using a temperature sensitive paint. This measurement technique represents a non-intrusive method to determine wall surface heat flux with a high spatial resolution. The application of this method to an internal flow, generated in a hydrogen fueled combustion wind tunnel model, is a new approach in the application of the measurement technique. The wind tunnel model represents the small scaled flight experiment configuration of the MR2 vehicle of the EU co-funded Long-Term Advanced Propulsion Concepts and Technologies project. The paper will discuss the special demands and prerequisites needed to apply TSP in high temperature flows. The experimental setup will be described and the feasibility of the application of TSP to internal flows and the resulting technical demands will be reviewed. The obtained result will be discussed with respect to the validity by comparison to a numerical simulation of the combustor flow