CPC F02C 7/047 (2013.01) [F05D 2220/323 (2013.01); F05D 2260/20 (2013.01)] | 11 Claims |
1. An air intake of a turbojet engine nacelle of an aircraft comprising a de-icing device and extending along an axis X in which an air flow circulates from upstream to downstream, the air intake annularly extending about axis X and comprising 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 and a front internal partition wall located inside the internal and external walls to delimit an annular cavity, the de-icing device comprising:
at least one hot air source in the annular cavity,
the internal wall, at an area upstream of the front internal partition wall, comprises a plurality of blowing lines,
the internal wall comprises at least one acoustic attenuation structure comprising a plurality of acoustic attenuation ports,
the acoustic attenuation ports being distributed on the internal wall outside the blowing lines and not configured to blow hot air,
each blowing line comprising a plurality of through openings configured to blow elementary flows coming from the at least one hot air source to de-ice said internal wall,
the plurality of blowing lines being parallel to each other in a cylindrical projection plane defined with respect to the axis X of the turbojet engine and to an axis Y defining the angular position with respect to the axis X,
each blowing line having a depth P3 defined along the axis X and a length L3 defined along the axis Y in the cylindrical projection plane,
two adjacent blowing lines being spaced apart by a distance D3 along the axis Y,
a distance ratio L3/D3 being between 1 and 2; and
wherein each blowing line is spaced by a tilt angle with respect to the axis X in the cylindrical projection plane, the tilt angle is between 20° and 70°.
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