Radially translating fan nozzle nacelle

A nozzle system for a gas turbine engine having a longitudinal axis, the nozzle system comprising:

• a fan duct inner wall;
• a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall;
• a fan nozzle defining at least a portion of the fan duct outer wall and having a nozzle aft edge, the fan duct inner wall and the nozzle aft edge collectively defining a fan duct throat area, the fan nozzle being configured to move outwardly relative to the longitudinal axis during axial translation thereof to vary the fan duct throat area, the fan nozzle being configured to move outwardly during axially aft translation and inwardly during axially forward translation between stowed and deployed positions;
• and
• a cowl assembly defining at least a portion of the fan duct outer wall;
• the fan duct outer wall being substantially continuous across the fan nozzle and the cowl assembly when the fan nozzle is moved between the stowed and deployed positions;
• the cowl assembly including a translating sleeve configured to move axially aft for thrust reversal;
• and
• the fan nozzle extending aftwardly from the translating sleeve and being movable between the stowed and deployed positions when the translating sleeve is moved axially aft.

An aircraft having a gas turbine engine with a longitudinal axis, comprising:

• a nozzle system including:
• a thrust reverser;
• a fan duct inner wall;
• a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, the fan duct inner and outer wall collectively defining a fan;
• and
• a fan nozzle defining at least a portion of the fan duct outer wall and having a nozzle aft edge defining a fan duct throat area relative to the fan duct inner wall, the fan nozzle being configured to non-pivotably move outwardly relative to the longitudinal axis during axially aft translation of the fan nozzle;
• the fan nozzle being movable without activating the thrust reverser, the thrust reverser having movable blocker doors configured to block fan flow through the fan duct when the thrust reverser is activated.

An aircraft having a gas turbine engine with a longitudinal axis, comprising:

• a nozzle system including:
• a fan duct inner wall;
• a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall;
• a fan nozzle defining at least a portion of the fan duct outer wall and having a nozzle aft edge, the fan duct inner wall and the nozzle aft edge collectively defining a fan duct throat area, the fan nozzle being configured to move outwardly relative to the longitudinal axis during axial translation thereof to vary the fan duct throat area, the fan nozzle being configured to move outwardly during axially aft translation and inwardly during axially forward translation between stowed and deployed positions;
• and
• a cowl assembly defining at least a portion of the fan duct outer wall;
• the fan duct outer wall being substantially continuous across the fan nozzle and the cowl assembly when the fan nozzle is moved between the stowed and deployed positions;
• the cowl assembly including a translating sleeve configured to move axially aft for thrust reversal;
• and
• the fan nozzle extending aftwardly from the translating sleeve and being movable between the stowed and deployed positions when the translating sleeve is moved axially aft.