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

Claim 7:
8. 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:
an injector comprising a mouthpiece extending along a mouthpiece axis, the mouthpiece comprising a housing having an upstream end and a downstream end having an outlet for directing air from the upstream end to the downstream end and out the outlet, a separating wall located inside the housing and extending along a length of the housing to define a first channel and a second channel within the housing, and a deflection member located only in the first channel; and
wherein the mouthpiece is configured to eject a first elementary stream in the first channel and a second elementary stream in the second channel in a superimposed manner so that the first and second elementary streams flow asymmetrically along the mouthpiece axis.