The aircraft gas turbine engine has an engine core (10) that is surrounded by a secondary flow channel (29). A side wall (30) is arranged radially outside the secondary flow channel. The radial inner wall (31) of the secondary flow channel is extended simi...

An exhaust nozzle assembly (18) for a gas turbine engine (10), the assembly (18) comprises a main axis (20), an inner nozzle (19), an outer nozzle (17), a translatable centre-body (44) and a means for translating the centre-body (49) between a forward posi...