Abstract:
The work is devoted to the numerical investigation of the flow of metalized fuel combustion
products in the rocket engine nozzle cluster. The system of equations for the gas-droplet environment
is written in the model of interpenetrating multispeed and multitemperature continua. The
condensed phase is represented by an ensemble of polydisperse liquid alumina particles. Coagulation
and fragmentation are taken into account due to the interaction both with each other and
with the gas. The description of condensate particle interaction is based on the continuous approach
of variation in the size distribution function.
The dependence of two-phase losses of the engine on the size of aluminum oxide particles due
to the nonequilibrium of the flow at the nozzle entrance is shown. Results of the numerical calculation
of the quasi-one-dimensional steady flow of aluminized fuel combustion products in the
profiled solid-fuel rocket engine nozzle are presented. Analysis of the calculation data suggests
that the use of high-dispersed aluminum powder in composite solid propellants increases the specific
impulse of the engine as compared to previously used powders.
Keywords:two-phase flow, particle size distribution function, polydisperse ensemble, coagulation and fragmentation of particles.
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