Journal of The Korean Society CombustionISSN:1226-0959(Print) 2466-2089(Online)한국연소학회

Need to improve the performances of the gas turbines and rocket engines are hindered by the limitations caused by melting points of the metallic super alloys at the combustor outlet nozzle or turbine components. High thermal resistive non-metallic materials are considered as future solutions to this problem. Most of these alternative non-metallic materials are carbon based composite materials and these materials can enable the gas turbines or rocket engines to operate at temperatures higher than the metallic super alloys. In this paper, a hydrocarbon fuel based evaluation system for carbon based composite materials is introduced. This evaluation system allows the testing and validation of the material specimens in a fuel burnt high thermal flow. The local Mach numbers were measured at five different locations using wedge probes in the flow's axial direction. The results reveal that the measured Mach numbers were almost constant about 1.4. The Mach number results indicate the flow generated by the evaluation system was stable and suitable for material evaluation.