Air intake and method for de-icing an air intake of a nacelle of an aircraft jet engine

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 pointing to axis X and an external wall which is opposite to the internal wall, the walls being connected by a leading edge and a front internal partition wall so as to delimit an annular cavity, the de-icing device comprising at least one hot air source in the annular cavity, the air intake being wherein the internal wall comprises a plurality of blowing lines, the internal wall comprising 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, each blowing line comprising a plurality of through openings configured to blow elementary flows coming from the hot air source in order to de-ice said internal wall, the blowing lines being parallel to each other in a cylindrical projection plane defined with respect to axis X of the turbojet engine and to an axis Y defining the angular position with respect to axis X, each blowing line having a depth P3 defined along axis X and a length L3 defined along axis Y in the cylindrical projection plane, two adjacent blast lines being spaced apart by a distance D3 along axis Y, the distance ratio L3/D3 being between 1 and 2.