Accession Number : AD0755879
Title : Propellant Spray Combustion Processes.
Descriptive Note : Final rept. Nov 70-Nov 72,
Corporate Author : ROCKETDYNE CANOGA PARK CALIF
Personal Author(s) : Sutton,R. D.
Report Date : JAN 1973
Pagination or Media Count : 60
Abstract : The purpose of this program was to define, through analysis and experiment, the mechanisms of energy addition from propellant-spray combustion to steady-flow fields and propagating pressure disturbances. Such information is important because it forms the basis of steady-state and transient propellant combustion models to accurately predict performance and combustion instability characteristics in liquid-propellant rocket and air-breathing engines and, thus, minimize the probability of encountering problems with these factors during engine development. A specialized model rocket engine was constructed to permit detailed observation of the spray-combustion processes occurring under well-defined conditions. The apparatus was designed to produce a monodisperse propellant spray uniformly distributed throughout the combustor. The motor could be operated under either stable or transient conditions and contained quartz windows on two sides to permit optical observation of the vaporizing droplets. (Author)
Descriptors : (*ATOMIZATION, EXPERIMENTAL DATA), (*LIQUID ROCKET PROPELLANTS, *COMBUSTION), INJECTORS, SPRAYS, FLOW FIELDS, ORIFICES, NOZZLE INSERTS, COLD FLOW, CAPTIVE TESTS
Subject Categories : Combustion and Ignition
Liquid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE