Numerical simulation of flow in a combustor with penetrable cavity wall

The results of numerical simulation of three configurations of a supersonic combustor are presented: without a cavity, with a solid rear wall of the cavity and a penetrable (discret) rear wall of the cavity. The calculations were carried out in a three-dimensional statement in the ANSYS calculation module with the parameters at the combustor entrance: the Mach number M = 2.89, the total pressure P0 = 2.84 MPa, the total temperature T0 = 2500 K. It is determined that the use of the rear walls of the cavity of both configurations leads to an increase in the static pressure and the static temperature along the whole length of the model channel. The preferred configuration is a cavity with a discrete rear wall that ensures the presence of zones with high flow parameters for ignition at a shorter length with less drag.