ANALYSIS OF LONGITUDINAL HIGH FREQUENCY COMBUSTION INSTABILITY IN A GAS FUELED ROCKET MOTOR

A theoretical investigation of the stability boundary for longitudinal high frequency oscillations in a gas fueled rocket motor has been carried out. It was based on the following assu ptions: (1) the mechanism responsible for combustion instability involves oscillatory heat transfer to the injector...

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Bibliographic Details
Main Authors: BORTZMEYER,HUBERT G, CROCCO,LUIGI
Format: Report
Language:English
Subjects:
COMBUSTION
COMBUSTION CHAMBER GASES
GASEOUS ROCKET PROPELLANTS
HEAT TRANSFER
HIGH FREQUENCY
INJECTORS
MATHEMATICAL ANALYSIS
OSCILLATION
POROUS MATERIALS
PRESSURE
ROCKET ENGINES
STABILITY
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Summary:A theoretical investigation of the stability boundary for longitudinal high frequency oscillations in a gas fueled rocket motor has been carried out. It was based on the following assu ptions: (1) the mechanism responsible for combustion instability involves oscillatory heat transfer to the injector plate; and (2) the rates of chemical reactions in homogeneous gas phase are high enough to enable the chemical system to respond without phase lag to periodic variations of the conditions in the chamber. Under these assumptions the equations governing the propagation of small pressure perturbations in the combustion chamber were derived, and oscillatory solutions of the type were found. By applying proper boundary conditions to these solutions a so-called characteristic equation for the unknown complex quantity s has been derived. Numerical solutions have been carried out for the relatively simple case of moderate frequency oscillations taking place in a chamber ended by a short nozzle. (Author)