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
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.
대표청구항▼
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
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); andat 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, andwherein 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); andan 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).
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이 특허에 인용된 특허 (5)
Porte, Alain; Lalane, Jacques, Acoustic treatment panel with integral connecting reinforcement.
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