Abstract: The reasonable choice of construction parameters for perforated acoustic liners in turbojet engine afterburners was investigated from the engineer's point of view. The perforated acoustic liner should have as much as possible high oscillation absorptivity in a quite wide frequency range by increasing the volume of acoustic resonant space and perforated area ratio of the shield. The smooth geometry of the liner can make the secondary flow uniform around the outer chamber shell and, therefore, avoid high temperature stripes proceeding from the gas separated-flow vortex at the wave valley on the perforated acoustic liner. Consequently, the circular temperature difference and the thermal stresses of the shell can be decreased, and the wall temperature of the afterburner shell can be kept down below the allowable temperature of its material. As a result, the afterburner can operate reliably for a long time.