A combustor model of a rocket-ramjet combined-cycle engine was tested in the ejector-jet mode under a sea-level, static condition. The model had two rockets in the duct. Propellants were gaseous hydrogen and oxygen. Design factor of the combustor were cross sections at the entrance and exit, length of the combustor, fuel injection position and rocket operating conditions. In the tests, the designed operation of the ejector-jet was successfully attained, that is, breathed air was choked at the throat section. Supersonic rocket exhaust and air were decelerated in the divergent duct with an increase of the wall pressure. Combustion gas choked at the exit. The mean combustion efficiency with 0.8 according to pitot pressure measurement and gas sampling. Suction performance was increased with an increase of the mixture ratio of the rockets. Pressure level in the model was affected by the length of the upstream straight section. The combustion status was not affected by the length of the downstream straight section or the position of fuel injection. An increase of fuel caused as increase of the pressure.
Experimental Study of a Combined-Cycle Engine Combustor in Ejector-Jet Mode
2008
14 pages
Report
Keine Angabe
Englisch
Combustion, Engines, & Propellants , Aeronautics & Aerodynamics , Space Technology , Combustion , Wall pressure , Performance evaluation , Propellants , Hydrogen , Oxygen , Design , Fuel injection systems , Cross sections , Rockets , Exhaust gases , Pressure management , Supersonic flow , Foreign technology
Experimental Study of a Combined-Cycle Engine Combustor in Ejector-Jet Mode
Online Contents | 2007
|Experimental Study of a Combined-Cycle Engine Combustor in Ejector-Jet Mode (AIAA 2006-0223)
British Library Conference Proceedings | 2006
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