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

Claim 13:
14. 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 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 within the housing;
wherein the separating wall is convergent from the upstream end to the downstream end such that the separating wall is smaller at the downstream end than the upstream end; 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.