A gas turbine engine is provided. The gas turbine engine includes a turbomachine (104); a fan section (102) including a fan (126) rotatable by the turbomachine (104); a nacelle (134) enclosing the fan (126); and an engine controller (150) positioned within...

An inner cowl arrangement (110) for a gas turbine engine (10) includes a first hinge (124) and a second hinge (126) pivotally connecting a first cowl member (112) and a second cowl member (118), respectively, to a mounting structure (106). The inner cowl a...

The assembly (1) has an air intake for sampling cooling air flow in secondary flow of a turbofan engine (6), and an air circulation pipe (60) for circulating air supplied by the intake. The intake is connected to the pipe and formed in an aerodynamic wall ...

The method involves discharging a part of a secondary air stream to reduce residual thrust of a turbofan (1). The air stream is discharged using a radial opening unit of an engine nacelle (9). The opening unit has an orifice (12) that is closed or opened b...

The engine has an air inlet structure (6) fixed to a fan casing (5), and a fan cover (7) and a thrust reverser cowl. A rod (48) and rigidifying complementary units (58, 60) are placed in the structure or between the cover and the cowl. The rod and units ar...