A duct for evacuating hot air from an aircraft engine is extended by a movable stack that can project from the wall such that the hot air is ejected a distance from the wall without risk of damaging the wall. The stack can, however, be retracted by a control device under circumstances of moderate engine speed, with the advantage that the drag of the wall, generally an outer nacelle, is then reduced.

A gas turbine engine designed to take-off and land as a conventional turbofan engine at subsonic speeds and accelerate to supersonic speeds during flight by converting into a hybrid turbojet and ramjet engine. This is achieved by introducing an afterburner in the bypass duct of the engine and by retracting the bypass fan backward into a cylinder. This operation is carried out before the aircraft enters the transonic regime, at any stage below Mach 1. At supersonic speed, the shock wave is deflected through a needle cone that is projected out of the nose of the engine in order to prevent the intake air from being choked.

A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.

A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.

A guide vane in an outer section of a turbofan engine contains oil cooling cavities which are located on one side of a main bending axis of the vane so that the differential thermal expansions compensate for the bending deformations caused by the aerodynamic forces exerted on the outer vane surface.

An integrated fan heat exchanger stator assembly is provided including a hub and a casing. A plurality of elements is arranged between the hub and the casing. The plurality of elements is separated from one another by a plurality of external flow passages. At least one internal flow passage is configured to convey a first heat transfer fluid through one or more of the plurality of elements. The first heat transfer fluid is arranged in thermal communication with a second heat transfer fluid configured to flow through at least one of the external flow passages.

An integrated fan heat exchanger stator assembly is provided including a hub and a casing. A plurality of elements is arranged between the hub and the casing. The plurality of elements is separated from one another by a plurality of external flow passages. At least one internal flow passage is configured to convey a first heat transfer fluid through one or more of the plurality of elements. The first heat transfer fluid is arranged in thermal communication with a second heat transfer fluid configured to flow through at least one of the external flow passages.

A turbine engine heat exchanger has: a manifold having a first face and a second face opposite the first face; a plurality of first plates along the first face, each first plate having an interior passageway; and a plurality of second plates along the second face, each second plate having an interior passageway. A first flowpath passing through the interior passageways of the first plates, the manifold, and the interior passageways of the second plates.

A duct for evacuating hot air from an aircraft engine is extended by a movable stack that can project from the wall such that the hot air is ejected a distance from the wall without risk of damaging the wall. The stack can, however, be retracted by a control device under circumstances of moderate engine speed, with the advantage that the drag of the wall, generally an outer nacelle, is then reduced.

A propulsion system for an aircraft. The propulsion system comprises a core, an internal fixed structure secured to the core and arranged around the core, and a nacelle surrounding the core and the internal fixed structure in which a secondary flow path is delimited between the internal fixed structure and the nacelle. The internal fixed structure has a slot which permits fluidic communication between a compartment on the inside of the internal fixed structure and the secondary flow path.