Numerical simulation of gas dynamics during operation of a wide-range rocket nozzle with a porous insert

When the rocket moves in the dense layers of the Earth’s atmosphere, classical nozzles operate in the jet overexpansion mode. In this mode, there is a partial decrease in the magnitude of the specifc impulse. As a result, the amount of fuel consumed by the rocket engine increases. An increase in the effciency of nozzle operation can be achieved by using designs of wide-range nozzles, in which case the replacement of a solid nozzle wall with a perforated one makes it possible to compensate for the loss of specifc impulse. The paper presents a study of the effect of a porous insert on the operating modes of the nozzle. Numerical simulation was performed in the Ansys Fluent software package. At the frst stage of the study, a geometric model of the computational zone is created which includes a two-dimensional model of the RD-107 rocket engine nozzle and a computational domain that simulates the external environment (air atmosphere). The calculation of the outfow of combustion products through the constructed nozzle at different pressures of atmospheric air is carried out. In the future, the classical nozzle is replaced by a nozzle with a porous insert, and the calculation is carried out at the same values of atmospheric pressure. The values of the specifc impulse obtained in calculations with a classical and porous nozzle are compared. The amount of fuel saved when replacing a classic nozzle with a porous one is determined by the difference in the areas bounded by the curves on the plot of specifc impulse versus the considered height above the Earth’s surface. Comparison of the values of the specifc impulse of nozzles with an impenetrable wall and a porous insert made it possible to conclude that up to a height of 5.4 km the specifc impulse of the nozzle with a perforated wall exceeds the values of the specifc impulse of the classical nozzle. Evaluation of the effectiveness of the use of a gas-permeable insert in the nozzle design when the nozzle operates in dense layers of the Earth’s atmosphere showed that with the start of operation at a height of 0 km above sea level and up to the height at which the nozzle operates in the design mode – the value of the compensated specifc impulse is 2.2 %. The results of the study can be applied in the design of nozzle devices of modern rocket engines operating in dense layers of the atmosphere.

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