Accession Number : AD0710312
Title : PARAMETRIC STUDY OF ROCKET MOTOR COMBUSTION INSTABILITY.
Descriptive Note : Final scientific rept.,
Corporate Author : PURDUE UNIV LAFAYETTE IND SCHOOL OF MECHANICAL ENGINEERING
Personal Author(s) : Osborn,John R.
Report Date : JUL 1970
Pagination or Media Count : 19
Abstract : The research program has been concerned with an experimental and analytical investigation conducted for evaluating the influence of combustion chamber pressure and propellant temperature effects on liquid rocket combustion dynamics. The experimental program was conducted with a small-scale rocket engine thrust chamber assembly using bi-phase propellants. Air was used as the oxidizer and normal heptane was used as the fuel. Chamber pressures investigaged ranged from 250 to 1000 psia; values below the critical pressure of the fuel to ones considerably above it. The values for the initial temperature of the injected fuel ranged from 520 to 910R. It was found that increasing the chamber pressure has a strong stabilizing effect, increasing the initial fuel temperature has a slight destabilizing effect, and decreasing the drop size has a strong destabilizing effect. Two combustion models were used for obtaining analytical predictions of the stability behavior for correlating the experimental results and for determining the validity of the models. General agreement was found between the experimental results and the analytical predictions. (Author)
Descriptors : (*LIQUID PROPELLANT ROCKET ENGINES, COMBUSTION), STABILITY, INJECTORS, ORIFICES, PRESSURE, COMBUSTION CHAMBERS, SCREAMING COMBUSTION, PREDICTIONS
Subject Categories : Combustion and Ignition
Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE