Flow of Combustion Products Containing Condensed-Phase Particles over a Recessed Vectorable Jet Nozzle

Волков, К. Н.; Denisikhin, S. V.; Emel’yanov, V. N.; Teterina, I. V.

doi:10.1007/s10891-017-1668-9

Cited by 2 publications

(1 citation statement)

References 13 publications

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“…For technological reasons, the subsonic part of the rotary nozzle is usually submerged into the combustion chamber (submerged nozzle). The immersion of the nozzle inside the pre-nozzle volume reduces the longitudinal size of the rocket, but generates a number of problems associated with the high-temperature flow of combustion products [7][8][9]. In a submerged nozzle, the impact of a two-phase flow of combustion products hits the frontal surface of the nozzle inlet, which poses the problem of organizing the flow in this area, excluding increased thermal and erosion effects [2].…”

Section: Introductionmentioning

confidence: 99%

Fluid Dynamics of Thrust Vectorable Submerged Nozzle

Denisikhin

Emel’yanov

Волков

2021

Fluids

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A numerical simulation of the gas-dynamic processes in the thrust vectorable nozzle of the solid rocket motor is considered. Construction of a geometric model and a generation of computational mesh, and reconstruction of model and mesh at each time step are discussed. Calculations of the flowfield of combustion products in the pre-nozzle chamber and nozzle block are carried out for various angles of nozzle rotation. The distributions of the gas dynamic quantities in the pre-nozzle volume corresponding to the outflow of the combustion products from the cylindrical channel and star-shaped channel are compared, as well as the solutions of the problem obtained with quasi-stationary and unsteady formulations. The effects of the channel shape on the distribution of flow quantities and formation of a vortical flow structure in the nozzle block are discussed.

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Section: Introductionmentioning

confidence: 99%