Back to results
US 8,074,440 B2Granted
Gas turbine engine with axial movable fan variable area nozzle
AssigneeUnited Technologies Corporation
InventorsGregory A. Kohlenberg, Sean P. Zamora
Life of this patent
Estimating the term…
Abstract
A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides aftward relative to the fixed first fan nacelle section to change the effective area of the fan nozzle exit area.
Claims15
A nacelle assembly for a high-bypass gas turbine engine comprising:
- a core nacelle defined about an engine centerline axis;
- a fan nacelle mounted at least partially around said core nacelle to define an annular fan bypass flow path;
- and
- a fan variable area nozzle in communication with said fan bypass flow path, said fan variable area nozzle having a first fan nacelle section and a second fan nacelle section, said second fan nacelle section axially movable relative said first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, said auxiliary port no more forward than 0.1 DEL_X/L_DUCT from a maximum radius of said annular fan bypass flow path, wherein DEL_X is the axial distance from said maximum radius to a forward most point of said auxiliary port and L DUCT is the axial length of said annular fan bypass flow path.
1 more element
A nacelle system for a high-bypass 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 to define a fan bypass flow path;
- and
- a fan variable area nozzle in communication with said fan bypass flow path, said fan variable area nozzle having a first fan nacelle section and a second fan nacelle section, said second fan nacelle section axially movable relative said first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, said auxiliary port no more forward than 0.1 DEL_X/L_DUCT from a maximum radius of said annular fan bypass flow path, wherein DEL_X is the axial distance from said maximum radius to a forward most point of said auxiliary port and L_DUCT is the axial length of said annular fan bypass flow path.
4 more elements
Dependencies are inferred from the claim text.