Coating for acoustic treatment integrating the function of frost treatment with hot air

1. Coating for acoustic treatment relative to an aircraft's surface, said coating comprises:

an acoustically resistive layer ( 28 ),

at least one alveolar structure ( 30 ), and

a reflective layer ( 32 ), wherein,

said alveolar structure ( 30 ) comprises a number of tubes that empty out, on the one hand, at a first imaginary surface ( 34 ), and, on the other hand, at a second imaginary surface ( 36 ), and

said alveolar structure ( 30 ) further comprises

i) sets of one or more tubes with side walls free of cut-outs and openings, and

ii) tubes with side walls having cut-outs ( 38 ) linking adjacent tubes so as to create a network of communicating tubes for communicating hot gas around one of the sets of one or more tubes with side walls free of cut-outs and openings,

wherein at least one of the communicating tubes is connected to at least one hot gas intake ( 40 ).

2. Coating for acoustic treatment according to claim 1 , wherein the alveolar structure ( 30 ) comprises a series of first non-secant bands ( 48 ) that are spaced apart, and at least one second series of second non-secant bands ( 50 ) that are spaced apart, and wherein the first bands ( 48 ) are secant with the second bands ( 50 ) so as to delimit a tube between, on the one hand, two first adjacent bands ( 48 ), and, on the other hand, two second adjacent bands ( 50 ).

3. Coating for acoustic treatment according to claim 2 , arranged at an air intake of an aircraft nacelle, wherein the first bands called longitudinal bands are arranged in radial planes that contain the longitudinal axis ( 18 ) of the nacelle.

4. Coating for acoustic treatment according to claim 2 , wherein each second band ( 50 ) called a transverse band is essentially perpendicular to the tangent at the second imaginary surface ( 36 ).

5. Coating for acoustic treatment according to claim 3 , wherein each longitudinal band ( 48 ) is essentially perpendicular to the tangent of each transverse band ( 50 ).

6. Coating for acoustic treatment according to claim 2 , wherein the longitudinal bands ( 48 ) comprise first cut-outs ( 52 ) that work with second cut-outs ( 54 ) that are provided at the transverse bands ( 50 ).

7. Coating for acoustic treatment according to claim 2 , wherein it comprises, on the one hand, first cells ( 66 ) that are dedicated to the channeling of hot air for the treatment of frost with small cross-sections, delimited by bands ( 48 , 50 ) that are brought close together, and second cells ( 68 ) that are dedicated to acoustic treatment with larger cross-sections, delimited by bands ( 48 , 50 ) with a larger spacing than that of the bands ( 48 , 50 ) that delimit the first cells.

8. Coating for acoustic treatment according to claim 1 , wherein it comprises a cavity or a channel ( 70 ), connected to a hot gas intake ( 40 ), arranged at a portion of the periphery of the alveolar structure, able to communicate with at least one cell ( 68 ) that is dedicated to the channeling of the hot gas.

9. Leading edge of an aircraft that incorporates a coating for acoustic treatment according to claim 1 .

10. Air intake of a nacelle of an aircraft that incorporates a coating for acoustic treatment according to claim 1 .

11. Coating for acoustic treatment according to claim 3 , wherein each second band ( 50 ) called a transverse band is essentially perpendicular to the tangent at the second imaginary surface ( 36 ).

12. Coating for acoustic treatment according to claim 4 , wherein each longitudinal band ( 48 ) is essentially perpendicular to the tangent of each transverse band ( 50 ).

13. Coating for acoustic treatment according to claim 11 , wherein each longitudinal band ( 48 ) is essentially perpendicular to the tangent of each transverse band ( 50 ).

14. Coating for acoustic treatment according to claim 3 , wherein the longitudinal bands ( 48 ) comprise first cut-outs ( 52 ) that work with second cut-outs ( 54 ) that are provided at the transverse bands ( 50 ).

15. Coating for acoustic treatment according to claim 3 , wherein it comprises, on the one hand, first cells ( 66 ) that are dedicated to the channeling of hot air for the treatment of frost with small cross-sections, delimited by bands ( 48 , 50 ) that are brought close together, and second cells ( 68 ) that are dedicated to acoustic treatment with larger cross-sections, delimited by bands ( 48 , 50 ) with a larger spacing than that of the bands ( 48 , 50 ) that delimit the first cells.

16. Coating for acoustic treatment relative to an aircraft's surface, said coating comprises:

an acoustically resistive layer ( 28 );

a reflective layer ( 32 ); and

an alveolar structure ( 30 ) delimited by a first imaginary surface ( 34 ) and by a second imaginary surface ( 36 ), the reflective layer ( 32 ) being connected to the alveolar structure at the first imaginary surface ( 34 ) and the acoustically resistive layer ( 28 ) being alveolar structure at the at the second imaginary surface ( 36 ),

the alveolar structure ( 30 ) comprised of tubes that empty out at the first imaginary surface and at the second imaginary surface, said tubes sealed by, on the one hand, the acoustically resistive porous layer, and, on the other hand, the reflective layer, so as to form cells,

the alveolar structure ( 30 ) further comprised of cut outs ( 38 ), wherein,

a first set of said tubes has side walls free of said cut-outs, the first set of said tubes defining non-communicating cells isolated from one another and having an acoustic function,

a second set of said tubes has side walls with said cut-outs ( 38 ),

the cut-outs link adjacent tubes of said second set of tubes so as to create a network of communicating tubes for communicating hot gas around one or more tubes of the first set of said tubes with side walls free of cut-outs, and

at least one tube of said first set of said tubes of the network of communicating tubes has a hot gas intake ( 40 ).