Aéronef (1) muni d'un turbomoteur (10) comprenant un générateur de gaz (15), le générateur de gaz (15) comprenant un ensemble de compression (20) alimentant en air une chambre de combustion (24) ainsi qu'un ensemble de turbine (25) alimenté en gaz par la chambre de combustion (24), l'aéronef (1)…

A method of controlling an aircraft gas turbine engine cooling system (20). The cooling system comprises a heat exchanger (22) having a first fluid path (24) through which fan air can flow, and a second fluid path (26) through which relatively hot compressor air can flow. The cooling system (20)…

Embodiments of a turboshaft engine (40) are provided, as are embodiments of a method for manufacturing a turboshaft engine. In one embodiment, the turboshaft engine includes an Inlet Particle Separator (IPS) system (42) having an IPS scavenge flow circuit (70, 102) fluidly coupled to the engine's…

The invention relates to aeronautical engineering and, more specifically, to air intakes for supersonic aircraft propulsion systems. The technical result to be achieved by the invention consists in ensuring stable operation of the engine in all flight regimes up to the maximum Mach number of M=3.0…

An air intake system suitable for a supersonic vehicle is disclosed. The system includes a channel comprising an inlet and a side wall and a plenum coupled to the side wall. The plenum is configured to accept a flow of coolant. In certain embodiments, the coolant is the waste coolant from an…

The housing (29) has a honeycomb structural layer arranged in a region of an inflow-side air inlet (11) at the housing arranged upstream of a fan (12). Sound proofing elements arranged at radially outside the honeycomb structural layer that extends in axial direction. The sound damping elements are…

A clamp suitable for use in an anti-icing system of a gas turbine engine is provided is disclosed. The clamp has a clasping portion for clasping a heating element. Two resilient arms extend from the clasping portion to a substantially rigid outer collar. Translational movement of the clasping…

The device has a first annular flange (50) connected to an air intake (42). A second annular flange (46) is connected to a motorization pipe (44) plated against the first flange. A connection element (56) comprises a wall arranged on a plane perpendicular to an axis of a nacelle comprising a…

The nacelle has a connecting device comprising an annular flange (46) that is connected to an air inlet (42), and another annular flange (50) connected to a motor (44) that is pressed against the former flange. The flanges extend in a plane perpendicular to a longitudinal axis of the nacelle…

The device has an annular flange (50) linked to an air intake, and another annular flange linked to an engine that is pressed-up against the former annular flange. A blade (66) is arranged between a fastening element (56) i.e. bolt, and the former annular flange. The blade comprises a central part…

The nacelle has two conduits connected together by a fastening device, which comprises two annular flanges (46, 50) respectively attached to an air inlet (42) and an engine (44). A fastening element (56) i.e. bolt, has rods (58) housed in respective passage holes (54). An angle profile (66) is…

A bird knocking-off rod of a bird knocking-off device is disposed outside a jet engine, in front of an air inlet of the jet engine and capable of rotating with a rotation area that is larger than an opening area of the air inlet of the jet engine. The rotary drive unit contains a rotary drive…

An example auxiliary power unit air inlet assembly (30;30a) includes a noise attenuating component (46;46a) disposed within a conduit (34;34a). The conduit is configured to communicate a first flow of fluid to an auxiliary power unit (14). A second flow of fluid is communicated to the noise…

The intake (18) has an annular internal shell (30) including fluid passage orifices, and an annular lip (24) connected to external and internal downstream edges (28, 32) of external shroud (26) and the shell, so as to form a leading edge of the intake. The shell has a portion (43) devoid of fluid…

A missile comprises a propulsion system, a passageway (1) for delivering air to the propulsion system and a ducting element (9) associated with the passageway (1). The ducting element (9) has a ducting surface for ducting air into the passageway (1), and the ducting element (9) is rotatable, about…

The nacelle has a lip (114) extended inside and outside the nacelle by inner and outer walls (116, 118), respectively. A front frame (122) connects the inner wall and the outer wall that delimits an annular pipe (124). A rear frame (126) connects the walls close to a motorization unit (112). A…

A fan nacelle (34) for a gas turbine engine includes a leading edge region (40) with a flow path (42) between an intake region (48) in a nacelle outer surface (44) and an exhaust region (50) in a nacelle inner surface (46) to locally modify a flow around the leading edge region (40) during a…

The inlet has a dynamic inlet duct (30) provided with a grid (40) for protection against ingesting foreign bodies. The grid is moved in translation along a dynamic axis (AX1) relative to a front flow section of the duct. A lateral inlet is arranged in a side wall. A covering unit (41) covering the…

A liner assembly (12) for a fan case (10) includes a noise attenuation layer (16) covered by a face sheet (18). The face sheet (18) includes openings (20) to the underlying noise attenuation layer (16). The face sheet (18) and noise attenuation layer (16) include acoustically transparent joints…

A gas turbine engine comprises a fan section (12), a compressor (14), a combustor (16) and a turbine (18) and includes a nacelle (22) having an inner nacelle surface (32) defining an inlet duct (42). The inner surface (32) is designed to reduce an inlet duct area (64) of the inlet duct to increase…

The assembly has an air inlet structure with an inner wall (32) having a sound wave attenuating acoustic structure (36, 38, 40). The wall has a protrusion part (32) extending backwards beyond a bond line (A) of a connecting flange (22) of an engine crankcase. The length of the part (32) is such…

The structure has an annular part which defines a fan case ducting that includes inner and outer casings (16, 17). A rigidifying bar (20) has ends (24, 22) integrated to the respective casings and to front and rear stiffening frames (18, 19) respectively. The ends (22, 24) are integrated to an…

In an aspect, a method is provided for attenuating jet engine noise. Air velocity, adjacent to an inlet fan duct outer wall (22), is increased to a greater rate than typical velocity of an operational engine ambient inlet airflow (12), adjacent to the inlet fan duct outer wall. Boundary layer (50)…

An air intake (10) includes a spike (11) and a cylindrical cowl (26). The spike is composed of a plurality of plates (22) which are arranged axial symmetrically around a central axis thereof, and the cowl includes an inner wall parallel to the central axis and is formed so as to enclose a rear…

The pod has a tubular air intake (6) comprising an acoustic-attenuation internal tubular piece (10) of resonator type. A tubular transition part (17), which has an acoustically homogeneous internal face, connects the air intake to a tubular fan casing (16). The internal face of the internal tubular…

Air inlet for a gas turbine engine with an active system (10) for the suppression of a ground vortex generated by the engine of an aircraft avoiding the vortex ingestion into the engine, the system includes an actuator assembly (14) in fluid communication with a fluid source; and, at least one…

The liner system (50) includes a mode-scattering segment (48) providing a reactance between -12 and -2 rho c and a sound absorbing segment (40) providing a reactance between -1 and -0 rho c, to provide a reactance discontinuity, such that mode-scattering of the sound field enables the sound…

The fence element has two posts connected by a transverse rail (3) supporting a number of vertical bars (5), the rail having U-shaped openings (31) that match the transverse cross-section of the bars formed by folding sheet metal. The bars can be partially engaged (F1) in the openings, and the bars…

The turboprop aircraft engine has an outer air intake (1) connected to an passage (2) supplying a compressor with air. The air intake passage can be helical along the longitudinal axis of the aircraft engine. The rotational angle of the helix is dependent on the propeller induced intake pressure…

An aircraft (10) comprises a wing (12) having an upper surface (16) and a lower surface (18) and at least one turbofan gas turbine engine (20) mounted on the wing (12). The axis (34) of the at least one turbofan gas turbine engine (20) is arranged substantially in the plane (14) of the wing (12) of…