The method involves guiding a fraction of primary flow (10) in an ignition zone (34) of an afterburner in order to maintain the temperature in the zone at a value greater than value of secondary flow (20) in a manner to favor ignition of the afterburner. T...

An aft FLADE gas turbine engine (1) includes a fan section (115) drivenly connected to a low pressure turbine section (150), a core engine (18) located between the fan section (115) and the low pressure turbine section (150), a fan bypass duct (40) circums...

The turbomachine has an annular bailer (11) provided around an upstream portion (10a) of a confluent sheet metal (3) to collect an airflow (F3) in a secondary cold flow (F2). The airflow is injected tangentially in a primary hot flow (F1) by a set of chann...

A lobe mixer (22) used in jet engines, is provided with diameter expansion portions (22a) in which the diameters gradually increase in the downstream direction, in which adjacent diameter expansion portions have different diameters from each other, and whi...

There is disclosed a lobe mixer comprising: a cylindrical partition wall 22 which partitions a high-speed inner flow from a low-speed outer flow; a lobe portion 24 which is disposed on a downstream side of the partition wall and whose transverse sectional ...

A gas turbine engine exhaust nozzle (18,22) includes an outlet (28,30) for discharging exhaust, and a plurality of circumferentially spaced apart stub airfoils (34) disposed adjacent the outlet. The airfoils shed vortices for mixing exhaust flow and attenu...