Accession Number : AD0614657
Title : PARAMETRIC STUDY OF ROCKET INSTABILITY.
Descriptive Note : Final rept.,
Corporate Author : PURDUE UNIV LAFAYETTE IND SCHOOL OF MECHANICAL ENGINEERING
Personal Author(s) : Zucrow,M. J.
Report Date : 17 FEB 1965
Pagination or Media Count : 8
Abstract : Research was conducted to determine those dimensionless parameters that may be employed as criteria for predicting the stability of combustion in a thrust chamber. UNMIXED GASEOUS PROPELLANTS: Unmixed propellants with impinging jet injectors yield combustion pressure oscillation similar to that obtained for premixed propellants with respect to fuel reactivity. BIPHASE PROPELLANTS (LIQUID FUEL-GASEOUS OXIDIZER): Investigations were conducted to determine the effects of (1) both the air and propellant injection velocities, chamber pressure, and fuel-air ratio on the steady-state operating characteristics of a rocket motor, and (2) selected parameters on propellant vaporization rate. CORRELATION OF RESULTS WITH SIMILARITY VARIABLES: Dimensionless parameters were derived that are sensitive to the occurrence of small amplitude pressure oscillations in the burning gaseous medium in a cylindrical combustion chamber. THEORETICAL ANALYSIS: An analysis was completed of the longitudinal combustion pressure oscillations for one model of the combustion zone.
Descriptors : (*ROCKETS, STABILITY), (*ROCKET ENGINES, COMBUSTION), (*COMBUSTION, ROCKET ENGINES), LIQUID ROCKET PROPELLANTS, GASEOUS ROCKET PROPELLANTS, AIR, GASES, OXIDIZERS, FUEL INJECTION, VAPORIZATION, INJECTION, COMBUSTION CHAMBERS, REYNOLDS NUMBER, THEORY, PRESSURE, CYLINDRICAL BODIES, OSCILLATION
Distribution Statement : APPROVED FOR PUBLIC RELEASE