Abstract: A method and a system (10) for exhausting gas via a nozzle (19, 21) of a gas turbine engine, for example. The system (10) comprises a nozzle (19, 21) comprising a nozzle body portion (32, 33, 74) defining a nozzle exit (42, 43), characterised in that the nozzle body portion (32, 33, 74) comprises fluid injection means (60), positioned upstream of the exit (42, 43) relative to a fluid flow (F1, F2) created by the operation of the system, for injecting fluid (68) upstream of the exit (42, 43).

Abstract: A gas turbine engine exhaust nozzle for reducing exhaust noise comprising a substantially frusto-conical nozzle wall, and a plurality of circumferentially disposed nozzle tabs which extend in a generally downstream direction from a downstream periphery of the nozzle wall. The nozzle tabs are radially inwardly angled at an angle (&bgr;) of up to 20°, but preferably up to 10°, relative to the nozzle wall. Preferably tabs are of a substantially trapezoidal shape and substantially trapezoidally shaped notches are defined between adjacent tabs. Substantially V shaped notches may however be defined between the tabs. The angled tabs are particularly suitable for a ducted fan gas turbine engine and can be provided on the core exhaust nozzle or the bypass exhaust nozzle or on both nozzles. A bypass exhaust nozzle with such angled tabs can also be used with a lobed core exhaust nozzle.