Cooled variable area nozzle for an aircraft engine

An apparatus for an aircraft engine, comprising:

• a variable area nozzle including a nozzle wall, a nozzle sleeve, an actuator 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 including a shell, a liner, an endwall, a cooling cavity and an aperture, the shell extending axially along and circumferentially about the axis, the liner axially overlapping and circumscribing the shell, the endwall extending radially between and connected to the shell and the liner at a downstream end of the liner, an inner radial end of the endwall connected to and contacting the shell, an outer radial end of the endwall connected to and contacting the liner, the cooling cavity extending longitudinally within the nozzle sleeve to the endwall, the cooling cavity formed by and between the shell and the liner, and the aperture extending through the endwall and fluidly coupling the cooling cavity to the flowpath;
• and
• the actuator operatively coupled to the nozzle sleeve and configured to move the nozzle sleeve axially along the axis relative to the nozzle wall.

An apparatus for an aircraft engine, comprising:

• a flowpath;
• a structure forming a radial peripheral boundary of the flowpath, the structure including a shell, a liner, a cooling cavity and an ejector, the liner axially overlapping and circumscribing the shell, the cooling cavity between and formed by the shell and the liner, the cooling cavity extending longitudinally within the structure to the ejector, the ejector arranged at a downstream end of the liner along the flowpath, the ejector fluidly coupling the cooling cavity to the flowpath, the ejector comprising a liner mount, an endwall and a shell mount, the shell mount projecting out from an inner radial end of the endwall, the shell mount connected to and in contact with the shell, and the liner mount projecting out from an outer radial end of the endwall, and the liner mount connected to and in contact with the liner;
• and
• a fluid source fluidly coupled to the cooling cavity, the structure configured to receive cooling air in the cooling cavity from the fluid source at a pressure that is less than a pressure of combustion products flowing in the flowpath along the liner.