Two-phase flows in Laval nozzles as a rule exhibit no symmetry and have definitely three-dimensional character. That is caused by specific shapes of the nozzles. Flows of combustion products in axially symmetric nozzles of modern rocket engines, which use solid propellant, can also be three-dimensional. That can be caused by non-symmetric character of propellant burning, non-symmetric character of boundary-layer separation in over-expanse regime of engine, complicated swirl law, etc. Studies of three-dimensional two-phase flows in nozzles are carried experimentally as well as by means of numerical simulations. Majority of theoretical works were based on multi-liquid model of the continuous medium without taking info account interactions of particles of different fractions. The simplified “monodisperse” model of particle breaking was used in works, where the processes of coagulation and breaking of particles were considered. Later A.A. Shraiber developed more physically realistic “polydisperse” model of particle breaking. The model had been realized for quasi-one-dimensional and axially symmetric flows. The “polydisperse” model of particle breaking for three-dimensional flow in Laval nozzle is firstly realized in the present work. Obtained results demonstrated qualitative difference in distribution of flow parameters compared to monodisperse” model of particle breaking. Rotation of condensate particles caused by their collisions is considered as well in this work.
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