A nine-month exploratory development program was conducted to analyze, design, fabricate, and test hardware to gather data on the operation of an expansion-deflection nozzle. The technical effort consisted of the analysis and design of a nominal 25,000-lb thrust, 1500 psia chamber pressure, expansion-deflection thrust chamber using LO2/LH2 propellants at a mixture ratio of 6:1. Several chamber segments and an annular uncooled thrust chamber were designed using an anticipated flight configuration thrust chamber design as a baseline. An annular and a segment injector were analyzed and designed for use on the thrust chambers. The segment injector and both water-cooled and heat sink chambers were fabricated and tested at sea level conditions. The injector demonstrated acceptable operation at chamber pressures of 300 and 750 psi.
Expansion-Deflection Nozzle
1972
221 pages
Report
No indication
English
Rocket Engines & Motors , Unconventional nozzles , Liquid propellant rocket engines , Rocket nozzles , Design , Manufacturing , Liquefied gases , Oxygen , Hydrogen , Annular nozzles , Stability , Analysis , Fuel injectors , Liquid rocket propellants , Pressure , Combustion chambers , Thrust , Heat sinks , Performance(Engineering) , Regenerative cooling , Heat transfer , Expansion deflection nozzles
Hydraulic analog for the expansion-deflection nozzle.
AIAA | 1967
|Experimental and CFD Analysis of the Expansion Deflection Nozzle
British Library Conference Proceedings | 2011
|