Aircraft nacelle including an optimised acoustic processing system
An aircraft nacelle including a pipe ( 32 ), a peripheral wall ( 34 ), a lip ( 36 ), and a front frame ( 38 ) connecting the peripheral wall ( 34 ) and the pipe ( 32 ) and forming with the lip ( 36 ) a space ( 50 ) in which the hot air that is provided for frost treatment can circulate, with the pipe ( 32 ) including a coating ( 44 ) for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element ( 52 ) made of a heat-conducting material inserted between the lip ( 36 ) and the pipe ( 32 ) ensuring the continuity of the aerodynamic surfaces of the lip ( 36 ) and the pipe ( 32 ) and the propagation of heat from the space ( 50 ) toward the rear of the nacelle, whereby the at least one element ( 52 ) includes a coating ( 54 ) for acoustic treatment that is made of a heat-resistant material.
1. An aircraft nacelle, comprising:
a pipe ( 32 );
a peripheral wall ( 34 );
a lip ( 36 );
a front frame ( 38 ) connecting the peripheral wall ( 34 ) and the pipe ( 32 ) and forming with the lip ( 36 ) a space ( 50 ) in which the hot air that is provided for the frost treatment circulates;
a composite material acoustic coating ( 44 ) on the pipe ( 32 ); and
at least one element ( 52 ) made of a heat-conducting material inserted between the lip ( 36 ) and the pipe ( 32 ) ensuring the continuity of the aerodynamic surfaces of the lip ( 36 ) and the pipe ( 32 ) and the propagation of heat from the space ( 50 ) toward the rear of the nacelle,
wherein said element ( 52 ) comprises a coating ( 54 ) for acoustic treatment that is made of a heat-resistant material, and
wherein the element ( 52 ) comprises a first part ( 82 ) that ensures the mechanical function and that connects the lip ( 36 ), the front frame ( 38 ), and the pipe ( 32 ), and a second part that is dissociable from the first part that ensures the function of the acoustic treatment.
2. The aircraft nacelle according to claim 1 , wherein the first part ( 82 ) comprises a cylindrical portion ( 86 ) whose diameter is greater than that of the pipe ( 32 ) in such a way as to form a cavity ( 84 ) that is open in the direction of the pipe of the nacelle and able to house a coating ( 54 ) for acoustic treatment whose acoustically resistive layer closes said cavity ( 84 ) and ensures the continuity between the lip ( 36 ) and the wall of the pipe ( 32 ).
3. The aircraft nacelle according to claim 2 , wherein the first part ( 82 ) comprises a junction part ( 92 ) that ensures the junction between the lip ( 36 ), the front frame ( 38 ), and the cylindrical portion ( 86 ).
4. The aircraft nacelle according to claim 2 , wherein the coating ( 54 ) for acoustic treatment comprises a reflective layer ( 102 ) that is distant from the cylindrical portion ( 86 ).
5. The aircraft nacelle according to claim 4 , wherein the coating ( 54 ) for acoustic treatment comprises an extension ( 112 ) toward the rear for making it integral with the composite material coating ( 44 ).
6. The aircraft nacelle according to claim 4 , wherein the coating ( 54 ) for acoustic treatment comprises an extension ( 110 ) toward the front that comes into the extension of the lip ( 36 ).
7. The aircraft nacelle according to claim 6 , wherein the junction part ( 92 ) comprises an extension toward the rear ( 116 ) that is distant from the extension ( 110 ) of the coating ( 54 ) for making it possible for the hot air to circulate from the space ( 50 ) in the direction of the pipe ( 32 ) via at least one outlet opening ( 120 ) at the extension ( 110 ).
8. The aircraft nacelle according to claim 7 , wherein the projections or wedges ( 122 ) are provided between the extensions ( 116 , 110 ) of the junction part ( 92 ) and the coating ( 54 ) for keeping them spaced.
9. The aircraft nacelle according to claim 8 , wherein a seal ( 123 ) is inserted between the extension ( 116 ) of the junction part and the front edge of the coating ( 54 ) for acoustic treatment.
10. The aircraft nacelle according to claim 9 , wherein a seal ( 123 ) is inserted between the extension ( 116 ) of the junction part and the front edge of the coating ( 54 ) for acoustic treatment.
11. The aircraft nacelle according to claim 7 , wherein a seal ( 123 ) is inserted between the extension ( 116 ) of the junction part and the front edge of the coating ( 54 ) for acoustic treatment.
12. The aircraft nacelle according to claim 5 , wherein the coating ( 54 ) for acoustic treatment comprises an extension ( 110 ) toward the front that comes into the extension of the lip ( 36 ).
13. The aircraft nacelle according to claim 12 , wherein the junction part ( 92 ) comprises an extension toward the rear ( 116 ) that is distant from the extension ( 110 ) of the coating ( 54 ) for making it possible for the hot air to circulate from the space ( 50 ) in the direction of the pipe ( 32 ) via at least one outlet opening ( 120 ) at the extension ( 110 ).
14. The aircraft nacelle according to claim 13 , wherein the projections or wedges ( 122 ) are provided between the extensions ( 116 , 110 ) of the junction part ( 92 ) and the coating ( 54 ) for keeping them spaced.
15. The aircraft nacelle according to claim 3 , wherein the coating ( 54 ) for acoustic treatment comprises a reflective layer ( 102 ) that is distant from the cylindrical portion ( 86 ).
16. The aircraft nacelle according to claim 15 , wherein the coating ( 54 ) for acoustic treatment comprises an extension ( 112 ) toward the rear for making it integral with the composite material coating ( 44 ).
17. An aircraft nacelle, comprising:
a pipe ( 32 );
a peripheral wall ( 34 );
a lip ( 36 ) located forward of the pipe ( 32 ) and the peripheral wall ( 34 );
a front frame ( 38 ) connecting the peripheral wall ( 34 ) and the pipe ( 32 ), and supporting the lip ( 36 ), the lip ( 36 ) extending forward from the peripheral wall ( 34 ) to the pipe ( 32 ) with the lip being forward of the front frame ( 38 );
a hot air space ( 50 ) delimited by the front frame ( 38 ) and the lip ( 36 ), the hot air space accommodating circulation of hot air provided for the frost treatment;
a composite material acoustic coating ( 44 ) on the pipe ( 32 ); and
an element ( 52 ) made of a heat-conducting material located rearward of the front frame ( 38 ) and the lip ( 36 ), and forward of the composite material acoustic coating ( 44 ) on the pipe ( 32 ) such that the element ( 52 ) made of a heat-conducting material is located between the lip ( 36 ) and the pipe ( 32 ) providing a continuity of the aerodynamic surfaces from the lip ( 36 ) to the pipe ( 32 ) and the propagation of heat from the hot air space ( 50 ) toward a rear of the nacelle, wherein said element ( 52 ) comprises an acoustic treatment coating ( 54 ) that is made of a heat-resistant material.
18. The aircraft nacelle according to claim 17 , wherein the element ( 52 ) comprises a first part ( 82 ) that provides a mechanical function and that connects the lip ( 36 ), the front frame ( 38 ), and the pipe ( 32 ), and a second part that is dissociable from the first part that ensures the function of the acoustic treatment.
19. The aircraft nacelle according to claim 18 , wherein the first part ( 82 ) comprises a cylindrical portion ( 86 ) whose diameter is greater than a diameter of the pipe ( 32 ) so as to form a cavity ( 84 ) that is open in the direction of the pipe ( 32 ) and houses the acoustic treatment coating ( 54 ) whose acoustically resistive layer closes said cavity ( 84 ) and ensures continuity between the lip ( 36 ) and the wall of the pipe ( 32 ).
20. The aircraft nacelle according to claim 19 , wherein the first part ( 82 ) comprises a junction part ( 92 ) that ensures the junction between the lip ( 36 ), the front frame ( 38 ), and the cylindrical portion ( 86 ).