A combustor was devised and tested for the application of a ram combustor in the propulsion system for super/hypersonic transport, aimed at flight Mach Numbers up to 5. Methane was selected as its fuel. The combustor comprises a gas turbine main combustion liner and a V-gutter flameholder. Design and testing was focused on the flight Mach 3 condition, when good combustion was expected to be difficult to achieve. Enhanced fuel-air mixing and flame-holding produced combustion efficiency of 99 % at the Mach 3 condition, while retailing low pressure loss.
Experimental studies on methane fueled ram combustor for super/hypersonic transport
Experimentelle Untersuchungen einer Staustrahl-Brennkammer für Methan als Treibstoff zum Einsatz in Überschall-/Hyperschalltransportflugzeugen
1995
8 Seiten, 17 Bilder, 1 Tabelle, 4 Quellen
Conference paper
English
Überschallgeschwindigkeit , Hyperschallgeschwindigkeit , Brennkammer , Stauaufladung , Staustrahltriebwerk , Methan , Treibstoff , experimentelle Untersuchung , Mach-Zahl , Gasturbine , Flammenhalter , Verbrennung (Oxidation) , Kraftstoff-Luft-Gemisch , Wirkungsgrad , Druckverlust , Transportflugzeug
Experimental Studies on Methane Fueled Ram Combustor for Super/Hypersonic Transport
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