Air intake structure for turbojet engine nacelle
An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural.
1. An air intake structure for a turbojet engine nacelle comprising:
a substantially annular main structure which comprises an internal wall, an external wall and an air intake lip wall connecting said external and internal walls upstream;
a first acoustic attenuation structure comprising a holed acoustic skin, a cellular core and a non-perforated rear skin with which said internal wall is equipped; and
a second acoustic attenuation structure comprising an architecture fitted to a part of the air intake lip wall substantially near a junction with the internal wall, wherein the non-perforated rear skin of the first acoustic attenuation structure is aligned with a non-perforated rear skin of the second acoustic attenuation structure, the non-perforated rear skins being structural so as to transfer forces between the air intake lip wall and the internal wall.
2. The air intake structure according to in claim 1 , wherein the air intake lip wall is integrated into the external wall.
3. The air intake structure according to claim 1 , wherein the second acoustic attenuation structure extends along the air intake lip wall at a leading edge zone with a sharp curvature of the air intake lip wall.
4. The air intake structure according to claim 3 , wherein in the leading edge zone, a thickness of the second acoustic attenuation structure progressively decreases.
5. The air intake structure according to claim 4 , wherein the thickness of the second acoustic attenuation structure decreases until the non-perforated rear skin of the second acoustic attenuation structure meets the external wall of the air intake structure.
6. The air intake structure according to claim 3 , wherein in the leading edge zone, the cellular core of the second acoustic attenuation structure is maintained by means of honeycomb studs.
7. The air intake structure according to claim 3 , wherein in the leading edge zone, the second acoustic attenuation structure has a discontinuous cellular core made from several sections, each having an appropriate curvature.
8. The air intake structure according to claim 1 , further comprising at least one structural gusset associated to the non-perforated rear skin of the second acoustic attenuation structure.
9. A turbojet engine nacelle comprises the air intake structure according to claim 1 .