An infrared suppressor adapted for use with a gas turbine engine includes a first ring arranged circumferentially around a axis, a second ring arranged circumferentially around the axis, and a strut that extends radially between and interconnects the first ring and the second ring. A portion of the second ring extends radially toward the first ring such that the portion of the second ring cooperates with the first ring to block line-of-sight into the infrared suppressor.

An infrared suppressor adapted for use with a gas turbine engine includes a first ring arranged circumferentially around a axis, a second ring arranged circumferentially around the axis, and a strut that extends radially between and interconnects the first ring and the second ring. A portion of the second ring extends radially toward the first ring such that the portion of the second ring cooperates with the first ring to block line-of-sight into the infrared suppressor.

An apparatus is provided for an aircraft engine. This apparatus includes a variable area nozzle. The variable area nozzle includes a nozzle wall, a nozzle sleeve, an actuation system and a flowpath extending axially along an axis through the variable area nozzle and radially between the nozzle wall and the nozzle sleeve. The nozzle sleeve includes a shell, a liner, a cooling cavity and an ejector. The shell extends axially along and circumferentially about the axis. The liner axially overlaps and circumscribes the shell. The cooling cavity is formed by and radially between the shell and the liner. The ejector is arranged at a downstream end of the liner along the flowpath. The ejector fluidly couples the cooling cavity to the flowpath. The actuation system is configured to move the nozzle sleeve axially along the axis relative to the nozzle wall.