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...

An air intake guide for a jet propulsion power plant for a supersonic aircraft comprises an intake aperture, an intake centre body and an intake adjustment device. The intake aperture has an intake lip, an intake centre body is positioned within the apertu...

A flade system for a gas turbine engine (12) is provided, wherein the gas turbine engine includes a core engine including an inner fan duct (28) for channeling airflow through a portion of the core engine, and at least one inner fan section (34) including ...

An airflow system for a gas turbine engine is provided, wherein the gas turbine engine includes a core engine (20), an inner fan assembly (22), and a fladed fan assembly (24). The airflow system includes a plurality of airflow ducts for channeling airflow ...

The bullet (24) is mounted on a shaft (10) by controlled units including a hydraulic jack (42) that displaces the axial position of the bullet with respect to fan blades (18). The cylinder of the jack is fixed at the end of the shaft, and the piston stem (...

The ramjet engine consists of an elongated body with two flat and parallel side walls, a fixed upper wall (4) and a sliding lower wall (5) with an obtuse-angled inverted V-section profile and front (11A, 11B) and rear (12) faces, an intake (16) for an oxid...