Air inlet shroud structure
The present invention relates to a nacelle for a turbojet, comprising an air inlet structure capable of channelling a flow of air to a turbojet fan and a middle structure ( 5 ) comprising a casing ( 9 ) designed to encircle said fan, with the air inlet structure attached to it, said structure having a peripheral inside surface at least partly equipped with a sound-attenuating structure ( 13 ) extending without geometrical interruption around at least part of the casing, said structure being characterized in that a gap ( 14 ) is provided between the sound-attenuating structure and the casing.
1. A nacelle for a turbojet comprising an air intake structure capable of channeling a flow of air toward a fan of the turbojet and a middle structure comprising a casing designed to surround said fan and to which the air intake structure is attached, an inner peripheral surface fixed to a sound attenuation structure, the sound attenuation structure extending downstream beyond the air intake structure with no geometric break, the sound attenuation structure extending over at least a portion of the casing, wherein a space is arranged between a top surface of the sound attenuation structure and the at least a portion of the casing, wherein the portion of the sound attenuation structure extending downstream beyond the air intake structure is not supported by the air intake structure.
2. The nacelle as claimed in claim 1 , wherein the sound attenuation structure comprises at least one structural reinforcement means.
3. The nacelle as claimed in claim 2 , wherein the structural reinforcement means comprise a sheath, fitted or incorporated into the sound attenuation structure.
4. A nacelle for a turbojet comprising an air intake structure capable of channeling a flow of air toward a fan of the turbojet and a middle structure comprising a casing designed to surround said fan and to which the air intake structure is attached, the latter having an inner peripheral surface at least partially fitted with a sound attenuation structure extending with no geometric break over at least a portion of the casing, wherein a space is arranged between the sound attenuation structure and the casing and wherein the sheath has, at the casing, a thickness that decreases in the direction of the fan.
5. The nacelle as claimed in claim 1 , wherein the sound attenuation structure is associated, at the casing, with at least one vibration-damping means.
6. The nacelle as claimed in claim 5 , wherein the at least one vibration damping means comprise at least one abutment system mounted on the casing and capable of preventing the sound attenuation structure from moving.
7. The nacelle as claimed in claim 5 , wherein the at least one vibration damping means comprise at least one elastic member mounted against the sound attenuation structure.
8. The nacelle as claimed in claim 6 , wherein the at least one vibration damping means are capable of coming into contact with the sound attenuation structure by means of at least one flexible stop.
9. The nacelle as claimed in claim 1 , wherein the sound attenuation structure has a downstream end capable of interacting with at least one complementary retention means fixedly attached to the casing.
10. The nacelle as claimed in claim 9 , wherein the complementary retention means comprises at least one post capable of interacting with at least one corresponding housing fitted or arranged in the downstream end of the sound attenuation structure.
11. The nacelle as claimed in claim 9 , wherein the casing has at least one binding strip capable of supporting the sound attenuation structure at its downstream end.