Gas turbine engine system and corresponding controlling method

A gas turbine engine system comprises a nacelle (28), a gas turbine engine (10) within the nacelle (28), and a fan bypass passage (30) between the nacelle (28) and the gas turbine engine (10). A nozzle (40) having a cross-sectional area is associated with a bypass air flow through the fan bypass passage (30), the nozzle (40) having at least one section (40a) that is selectively moveable between a plurality of static positions for varying the cross-sectional and at least one thrust reverse position that is different from the plurality of static positions for reversing a direction of the bypass flow of the fan bypass passage (30). The system further comprises a controller (44) for selectively moving the at least one section (40a) responsive to one of a plurality of operational states of the gas turbine engine (10).