Abstract
Physicomathematical models of multivelocity and multitemperature two-phase flows are suggested. The analyses take into account the particle rotation due to off-center collisions in solid rocket motor (SRM) nozzles and the effects of crossing the trajectories of other particles in the combustion chamber. The rotation of particles is treated by means of quasi-one-dim ensional approximation. The effect of the rotation on particle-size distribution and two-phase losses is shown. Three-dimensional two-phase flows in SRM nozzles with rectangular cross sections are considered. The influence of nozzle geometry on the gasdynamic structure of two-phase flow is determined. Axisymmetric calculations are performed for the flows in the combustion chambers and nozzles of SRM. The calculations show the importance of taking into account the intersection of particle trajectories in investigating flows in motors with charges of complex geometry. Nomenclature A = number of particle collisions a = sound velocity c = specific heat cp = specific heat of gas at constant pressure d = particle diameter d4:, = mass mean particle diameter E = total energy of unit volume
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