GAS TURBINE ENGINE

A gas turbine engine (100) includes a core engine casing (114) and a bypass duct (122) defined between a nacelle (106) and the core engine casing (114). The gas turbine engine (100) further includes a plurality of diverter fences (130) pivotally coupled to the core engine casing (114). Each diverter fence (130) is pivotable relative to the core engine casing (114) about a pivot axis (P), which is circumferentially and obliquely inclined with respect to a principal rotational axis (102). Each diverter fence (130) is configured to move between a first position (X1) in which an outboard edge (138) is disposed adjacent to a casing outer surface (120), and a second position (X2) in which the outboard edge (138) is radially spaced apart from the casing outer surface (120), such that each diverter fence (130) radially extends outwards from the casing outer surface (120) into the bypass duct (122).