A novel hydrogen-fueled jet stabilized combustor for application in a hypersonic flight vehicle was investigated. Experimental and numerical investigations were carried out to arrive at the optimum design. Eight models were selected for combustion tests at air inlet temperature of 600 K. One of the selected models was also tested at elevated air inlet temperatures. It was found that the transverse fuel supply to the air jet was effective to get the highest combustion efficiency but it caused high pressure loss. The other alternative is to arrange the air injectors in tandem. It was found that when the mixture strength was close to the stoichiometric, the combustion efficiency deteriorated to 90 %.
Investigations of hydrogen-fueled turbo-ramjet engine combustors with jet stabilized flames
Untersuchungen von Brennkammern mit Flammen-Strahlstabilisierung für Wasserstoff als Treibstoff zum Einsatz in Turbinen-Staustrahltriebwerken
1995
10 Seiten, 18 Bilder, 2 Tabellen, 7 Quellen
Conference paper
English
Staustrahltriebwerk , Gasturbine , Brennkammer , Flamme , Stabilisierung , Wasserstoff , Treibstoff , Luftfahrzeug , Hyperschallgeschwindigkeit , experimentelle Untersuchung , Auslegung (Dimension) , Optimierung , Modell , Lufteinlauf , Temperatur , Verbrennung (Oxidation) , Wirkungsgrad , Druckverlust , Stöchiometrie , Luftdüse
Investigations of Hydrogen-Fueled Turbo-Ramjet Combustors with Jet Stabilized Flames
British Library Conference Proceedings | 1995
|British Library Conference Proceedings | 1997
|Test Results of the Hydrogen Fueled Model Combustor for the Air Turbo Ramjet Engine
British Library Conference Proceedings | 1993
|Computer Modeling in Ramjet Combustors
AIAA | 1981
|