Pivoting fan nozzle nacelle
AssigneeThe Boeing Company
InventorMark E. Howe
Life of this patent
Estimating the term…
Abstract
A variable area nozzle system for a gas turbine engine includes a fan duct inner wall, a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, and a fan nozzle. The fan nozzle defines at least a portion of the fan duct outer wall and includes a nozzle aft edge. The fan duct inner wall and the nozzle aft edge collectively define a fan duct nozzle throat area. The fan nozzle is configured to pivot about a pivot axis that may be oriented transversely relative to a longitudinal axis of the gas turbine engine. The fan nozzle may be pivoted from a stowed position to a deployed position in order to vary the fan duct nozzle throat area.
Claims16
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;
- and
- 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 nozzle throat area, the fan nozzle being configured to pivot about a pivot axis oriented transversely relative to the longitudinal axis to vary the fan duct nozzle throat area;
- fan nozzle being configured to move axially independent of the pivoting of the fan nozzle.
An aircraft having a gas turbine engine with a longitudinal axis, comprising:
- a nozzle system for the gas turbine engine, including:
- a fan duct inner wall;
- a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall;
- and
- 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 nozzle throat area, the fan nozzle being configured to pivot about a pivot axis oriented transversely relative to the longitudinal axis to vary the fan duct nozzle throat area;
- fan nozzle being configured to move axially independent of the pivoting of the fan nozzle.
An aircraft having a gas turbine engine with a longitudinal axis, comprising:
- a nozzle system for the gas turbine engine, including:
- a fan duct inner wall;
- a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall;
- and
- 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 nozzle throat area, the fan nozzle being configured to pivot about a pivot axis oriented transversely relative to the longitudinal axis to vary the fan duct nozzle throat area;
- the fan nozzle including a cowl outer panel and a cowl inner panel disposed in radially spaced relation to the cowl outer panel;
- the cowl outer and inner panels having at least one cascade segment radially disposed therebetween;
- the cascade segment being configured to remain stationary when the fan nozzle is pivoted outwardly.
Dependencies are inferred from the claim text.