Back to results
US 2009/0288387 A1Published application
Gas turbine engine bifurcation located in a fan variable area nozzle
AssigneeUnited Technologies Corporation
InventorConstantine Baltas
Life of this patent
Estimating the term…
Abstract
A turbofan engine pylon structure having a fan variable area nozzle defined by a variable area flow system between a pylon intake and a pylon exhaust to selectively adjust a bypass flow. The variable area flow system changes the physical area and geometry of a fan nozzle exit area to manipulate the bypass flow by opening and closing an additional flow area of the variable area flow system.
Claims17
A nacelle assembly for a gas turbine engine comprising:
- a core nacelle defined about an axis;
- a fan nacelle mounted at least partially around said core nacelle;
- a pylon mounted to said core nacelle and said fan nacelle, said pylon having a variable area flow system in communication with a flow passage to control a volume of bypass flow through said pylon and vary a fan nozzle exit area, said variable area flow system movable toward an open position to increase said fan nozzle exit area and toward a closed position to decrease said fan nozzle exit area.
A gas turbine engine comprising:
- a core engine defined about an axis;
- a gear system driven by said core engine;
- a turbofan driven by said gear system about said axis;
- a core nacelle defined at least partially about said core engine;
- a fan nacelle mounted at least partially around said core nacelle;
- and
- a pylon mounted to said core nacelle and said fan nacelle, said pylon having a variable area flow system in communication with a flow passage to control a volume of bypass flow through said pylon and vary a fan nozzle exit area defined between said fan nacelle and said core nacelle, said variable area flow system movable toward an open position to increase said fan nozzle exit area and toward a closed position to decrease said fan nozzle exit area.
4 more elements
A method of varying a fan nozzle exit area of a gas turbine engine comprising the steps of:
- (A) varying a variable area flow system in communication with a flow passage through an engine nacelle pylon to change a volume of bypass flow through the engine nacelle pylon and control a fan nozzle exit area defined between a fan nacelle and a core nacelle in response to a flight condition, said variable area flow system movable toward an open position to increase said fan nozzle exit area and toward a closed position to decrease said fan nozzle exit area.
Dependencies are inferred from the claim text.