Variable area nozzle for an aircraft engine

An apparatus for an aircraft engine, comprising:

• a variable area nozzle including a nozzle inner structure, a nozzle outer structure, an actuation system and a flowpath extending axially along an axis through the variable area nozzle and radially between the nozzle inner structure and the nozzle outer structure;
• the nozzle inner structure including a nozzle wall and a nozzle sleeve, the nozzle wall extending axially along and circumferentially around the axis, the nozzle wall comprising a plurality of slots arranged circumferentially about the axis, each of the plurality of slots projecting radially through the nozzle wall, and the nozzle sleeve axially overlapping and circumscribing the nozzle wall;
• and
• the actuation system including a carriage and an actuator, the carriage including a hub, a plurality of struts, an inner platform, and an inner bearing, the plurality of struts arranged circumferentially about and connected to the hub, each of the plurality of struts projecting radially through a respective one of the plurality of slots wherein the nozzle sleeve is attached to the carriage at an outer end of the carriage, the actuator disposed radially within the inner nozzle wall and coupled to the hub, and the actuation system configured to move the nozzle sleeve axially along the nozzle wall;
• wherein the inner platform is radially inboard of the nozzle wall with each of the plurality of struts projecting radially out from the inner platform;
• and
• wherein the inner bearing is radially between and engaged with the inner platform and the nozzle wall.