This paper describes experimental studies of two flameholder configurations for a hydrogen fueled experimental subsonic ramjet combustor applicable to a hypersonic transport propulsion system. An experimental ramjet combustor with optical access was designed and manufactured. Two different flameholder configurations were tested at ambient pressure and at different inlet temperatures up to 700 K using non vitiated air. The hydrogen fuel was injected in the gaseous phase and tests were run up to equivalence ratios of 0.74. Combustion characteristics such as species concentrations of H2, O2, N2 and NO(x), gas velocities and pressures were measured inside the combustor to understand the turbulent combustion process as well as to obtain experimental data for validation of numerical simulations. For the second flameholder configuration axial turbulent vortices were introduced which, together with increased fuel penetration, improved the fuel distribution and enhanced the fuel/air mixing. This resulted in a significant improvement in combustion performance.
Experimental comparison of two flameholder configurations for a hydrogen fueled ramjet combustor
Experimenteller Vergleich von zwei Flammenhalterkonfigurationen für eine Staustrahl-Brennkammer mit Wasserstoff als Treibstoff
1995
10 Seiten, 12 Bilder, 2 Tabellen, 16 Quellen
Conference paper
English
Flammenhalter , Konfiguration , Brennkammer , Staustrahltriebwerk , Wasserstoff , Treibstoff , Unterschallgeschwindigkeit , experimentelle Untersuchung , Vergleichsmessung , Hyperschallgeschwindigkeit , Lufteinlauf , Temperatur , Gasdruck , Turbulenz , Simulation , numerisches Verfahren , Transportflugzeug
Experimental Comparison of Two Flameholder Configurations for a Hydrogen Fueled Ramjet Combustor
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