A bypass gas turbine engine (10) includes a variable area fan nozzle (42) with a second fan nacelle section (54) axially movable relative to a first fan nacelle (52) section to define an auxiliary port to vary a fan nozzle exit area (44) and adjust fan bypass airflow. The second fan nacelle section (54) includes a leading edge region (54L) that defines a concave external contour and the first fan nacelle section (52) includes a trailing edge (52T) region that defines a convex internal contour.
Gas turbine engine with variable area fan nozzle
Gasturbinenmotor mit verstellbarer Fandüse
Moteur à turbine à gaz doté d'une section de soufflante variable
2019-07-10
Patent
Electronic Resource
English
GAS TURBINE ENGINE WITH AXIAL MOVABLE FAN VARIABLE AREA NOZZLE
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