A method is provided for manufacturing during which a first duct section is formed with a tubular first sidewall. A first opening extends through the tubular first sidewall. The forming of the first duct section includes disposing a first woven fiber sleeve over a first mandrel and disposing a polymer material with the first woven fiber sleeve. A second duct section is disposed with a tubular second sidewall. The forming of the second duct section includes disposing a second woven fiber sleeve over a second mandrel and disposing the polymer material with the second woven fiber sleeve. The second duct section is arranged with the first duct section. The second duct section engages the tubular first sidewall. The tubular second sidewall is located at and extends circumferentially around the first opening. A duct structure is formed by attaching the second duct section to the first duct section.

An aircraft engine assembly can include an engine having an exhaust turbine with drive shaft and exhaust collector, a propeller rotationally coupled to the drive shaft and defining a rotational axis, and an exhaust stub to direct exhaust gases away from the aircraft.

The invention relates to a turbomachine (24) of the open rotor type or a turboprop engine comprising a nacelle (26) defining an air inlet (28), a central hub (30) and an annular air intake section (32) surrounding the central hub (30) and opening into a air supply main section (34), with the central hub (30) comprising a central trap (36) having an aperture (38) for trapping the foreign objects in an air flow entering the turbomachine (24), and an air recovery channel (48) having a discharge end (48a), through which said air recovery channel (48) opens into the main section (34), provided on the central hub (30).

An aircraft intake duct for channeling a flow of ambient air toward an annular engine compressor inlet of a gas turbine engine having a compressor reference axis and a reference plane that extends from such compressor reference axis. The aircraft intake duct includes an oblong air intake inlet for receiving the flow of ambient air, the air intake inlet being offset radially outwardly relative to the compressor reference axis and located on a first side of the reference plane. Two distal intake channels fluidly link distal extremities of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a second side of the reference plane. A central channel fluidly links a central section of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a first side of the reference plane. The distal channels are blended together by the central channel so that a single intake duct is formed.

An aircraft having a static air inlet system. The static air inlet system comprises a static air intake, the static air intake having a through opening formed in a top structural assembly, the through opening forming an interface between a medium and an inside space of the top structural assembly. The static air inlet system has at least one separator subdividing the through opening into at least two distinct slots, the separator comprising a first portion extended by a second portion, the first portion extending inside the inside space and the second portion extending outside the inside space.

An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.

An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.

An apparatus for providing foreign object debris protection an air intake of an aircraft engine. The apparatus includes a frame and a plurality of cross-members. The cross-members are positioned in the frame to define a plurality of screen openings. At least one of the cross-members has an aerodynamically efficient cross section.

An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The air intake may comprise a scroll portion and a strutted portion configured to receive the flow of air from the intake duct and channel the flow of air toward the intake outlet. The strutted portion may comprise one or more vanes for interacting with the flow of air. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.

A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.