Abstract: A by-pass gas turbine engine including a primary and a secondary nozzle which are substantially convergent, wherein the primary nozzle is situated radially within, but axially protruding from, the secondary nozzle characterised in that the primary and secondary nozzles have a substantially common central axis along their lengths and the direction of airflow exiting at least one of the primary or secondary nozzles is at an angle to the central axis of the engine and that the direction of airflow exiting each nozzle is at an angle to the other thereby promoting preferential distribution and mixing of the airflows. The end of both the primary and secondary nozzles may be truncated at oppositely orientated oblique angles. The internal profile of one or both nozzles may be arranged such that the airflow leaves the that nozzle at an angle to the axis of the nozzle.

Abstract: A by-pass gas turbine engine including a primary and a secondary nozzle which are substantially convergent, wherein the primary nozzle is situated radially within, but axially protruding from, the secondary nozzle characterized in that the primary and secondary nozzles have a substantially common central axis along their lengths and the direction of airflow exiting at least one of the primary or secondary nozzles is at an angle to the central axis of the engine and that the direction of airflow exiting each nozzle is at an angle to the other thereby promoting preferential distribution and mixing of the airflows. The end of both the primary and secondary nozzles may be truncated at oppositely orientated oblique angles. The internal profile of one or both nozzles may be arranged such that the airflow leaves the that nozzle at an angle to the axis of the nozzle.