A gas turbine engine inlet anti-ice system includes a nacelle having an inlet lip, an anti-ice air supply duct, and a flow deflector. The inlet lip has an annular anti-icing chamber formed therein that is defined by an inner surface of the inlet lip and an aft wall that has an aft wall opening…
Lèvre d'entrée d'air de nacelle de moteur d'aéronef pourvue d'un dispositif d'obturation passif d'orifice de communicationL'invention a pour objet une lèvre d'entrée d'air (12) de nacelle (10) de moteur d'aéronef pourvue d'un dispositif d'obturation passif (22) de dispositifs d'échappement (20). Le…
The nacelle has a lip (34) that is prolonged by an interior pipe (36) forming an air intake part. A front frame (32) delimits the lip, and an annular pipe (40) is utilized for circulation of hot air. An acoustic treatment panel (30) includes a set of stabilization chambers (62, 62'), and the…
The nacelle has a lip (34) prolonged by an interior pipe (36) forming an air intake. A front frame (32) delimits an annular pipe (40) in which hot air circulates and an acoustic treatment panel with the lip. The acoustic treatment panel includes upstream channels (50) and an annular channel (62)…
The nacelle has a lip prolonged by an interior pipe forming an air intake. A front frame delimits an annular duct (40) in which hot air circulates, and a panel treats sound from an outer side toward an inner side of an acoustically resistive layer. A pipe (98) is provided with an opening (100)…
The method involves deforming a layer i.e. sheet metal made of titanium alloy so as to produce furrows at one of surfaces of the layer. The deformed layer is flattened and integrated with an acoustically resistive layer (24) so as to border channels (30) of the resistive layer. A material is…
The device has an annular tubular element (31) extended along a circumferential direction. The tubular element comprises outflow openings for supplying hot air to a ring lip region (29) of a double-walled nacelle (30) for removing snow and ice. The tube element is formed with pipe segments along…
There is presented an air inlet cowl for a jet engine provided with de-icing means comprising an air extraction opening (34) made in the partition (20), to put into communication the insulation volume (28) enclosing the hot pressurized air supply duct (10) with the internal peripheral chamber (21)…
The jet engine air intake cowling comprises an air intake lip (6a), a de-icing system (10) and acoustic attenuation means (11). The acoustic attenuation means are constituted by separate islets (11a) each formed from a sandwich comprising a resistive acoustic porous layer forming a part of the fan…
The air intake cowling (9) for a jet engine, whose leading edge (16) is hollow and traversed by a hot air flow for de-icing (17), comprises outlets for the hot air flow to the outside of said leading edge (16), which form an arrangement (18) such that at least two jets of hot pressurized air…
An inlet ice protection system (60), and methods for making and using ice protection systems. The inlet (50) includes an acoustic liner (70a,70b) having a perforated face sheet (71a,71b), a perforated back sheet (72a,72b), and an acoustic core (75a,75b) between the face sheet and the back sheet…