Patent ID: 11879390
Assignee: SAFRAN NACELLES
Field: Transport (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 0:
1. A deicing device for an air intake of a nacelle of an aircraft turbojet engine extending along an axis X in which an air stream circulates from upstream to downstream, the air intake comprising an internal cavity annularly extending about the axis X, which comprises an internal wall facing the axis X and an external wall, which is opposite to the internal wall, the internal and external walls being connected by a leading edge, the deicing device comprising:
at least one injector for injecting a hot air stream into the internal cavity, the at least one injector comprising a mouthpiece extending along a mouthpiece axis;
wherein the mouthpiece comprises a housing having a separating member located therein to separate the mouthpiece between a first channel and a second channel, the first channel configured to lead a first elementary stream and the second channel configured to lead a second elementary stream and the first and the second elementary streams combine to form the hot air stream;
the mouthpiece being configured to eject the first elementary stream and the second elementary stream in a superimposed manner so that the hot air stream flows asymmetrically along the mouthpiece axis so as to generate turbulence in a vicinity of the external wall while heating the internal wall; and
wherein an air deflection member is located in the first channel.