Abstract

For simulation of turbulent flows the equations of the turbulent model are added to the general set of equations describing the flow in the Laval nozzle. There are several models of turbulence based on the use of Reynolds equations, which differ in approaches to the description of flow in the near-wall region, the number and physical meaning of additional unknown variables that determine the characteristics of turbulent flow. The flow in the nozzle with an obstacle is characterized by the appearance of developed separation zones with compaction jumps and significant gradients of velocity and pressure.

The calculations showed that the use of different turbulence models to the flow simulation in the classical Laval nozzle with the ANSYS software package does not significantly affect the flow characteristics. The perturbation mechanisms of the supersonic flow with a cylindrical solid obstacle mounted on the wall of the rocket engine nozzle in the throat and supersonic zones are studied. The results of using different turbulence models for perturbed flow are analyzed. It is shown that the TR-SST model, as a combination of the k-ε and k-ω models, is the most adequate to describe the perturbed flow in the nozzle of a rocket engine.

Keywords: Keywords: Eengine; Laval nozzle; Obstacle; Gas flow disturbance; Lateral force