The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section (7), said rear section having an internal structure (7b) inten
The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section (7), said rear section having an internal structure (7b) intended for serving as a housing to a rear portion of the turboreactor, characterized in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon (12) intended to be connected to a fixed structure (13) of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle.
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1. A nacelle for a turbofan comprising a front air intake section,a mid-section designed to surround a fan of a turbojet anda rear section, said rear section having an internal structure designed to serve as a casing to rear portion of the turbojet and an external structure,wherein the internal stru
1. A nacelle for a turbofan comprising a front air intake section,a mid-section designed to surround a fan of a turbojet anda rear section, said rear section having an internal structure designed to serve as a casing to rear portion of the turbojet and an external structure,wherein the internal structure has coupling means suitable for allowing an attachment of the nacelle to a pylon designed to be connected to a fixed structure of an aircraft on at least one portion of said internal structure,wherein the internal structure comprises at least one external wall forming an aerodynamic surface adjacent a cold flow stream that flows between the internal structure and the external structure, the external wall mounted over a framework made from plurality of radial frames distributed over the length of the internal structure and each radial frame comprising a circumferential ring,wherein each adjacent circumferential ring is connected together by at least one reinforcement between them. 2. The nacelle as claimed in claim 1, wherein the internal structure is fitted with means for rigid connection to the turbojet. 3. The nacelle as claimed in claim 1, wherein the internal structure is connected to the mid-section by means of a casing surrounding the fan. 4. The nacelle as claimed in claim 3, wherein the internal structure is connected to the mid-section of the downstream portion of the casing surrounding the fan on at least a portion of its periphery. 5. The nacelle as claimed in claim 4, wherein the internal structure is connected to the mid-section of the downstream portion of the casing over the whole of its periphery. 6. The nacelle as claimed in claim 4, wherein the peripheral groove of the casing has a V-shaped internal profile. 7. The nacelle as claimed in claim 6, wherein the framework comprises at least one longitudinal reinforcement on either side of a longitudinal axis of the internal structure. 8. The nacelle as claimed in claim 1, wherein the internal structure is fitted with a means for recentering the turbojet. 9. The nacelle as claimed in claim 1, wherein the internal structure is designed so that the pylon can extend over the whole length of the internal structure. 10. The nacelle as claimed in claim 1, wherein the pylon is incorporated into the internal structure. 11. The nacelle as claimed in claim 1, wherein the framework totally surrounds the turbojet. 12. The nacelle as claimed in claim 1, wherein the external wall is partially or totally made from at least one acoustic panel. 13. The nacelle as claimed in claim 1, wherein the radial frames are made from force-absorbing link rods. 14. The nacelle as claimed in claim 1, wherein at least a portion of the radial frames are made in a single piece. 15. The nacelle as claimed in claim 1, wherein at least a portion of the radial frames are made from several elements linked together, for example by bolting. 16. The nacelle as claimed claim 1, wherein the framework comprises at least one front radial frame and one rear radial frame connected by an intermediate structure forming a mesh. 17. The nacelle as claimed in claim 16, wherein the intermediate structure is made in the form of a caisson. 18. The nacelle as claimed in claim 16, wherein the intermediate structure is made from link bars connecting at least two radial frames together. 19. The nacelle as claimed in claim 18, wherein at least a portion of the link bars are incorporated into at least one radial frame. 20. The nacelle as claimed in claim 18, wherein the link bars are hollow. 21. The nacelle as claimed in claim 18, wherein the link bars are placed relative to one another so as to form triangles, preferably isosceles triangles. 22. The nacelle as claimed in claim 1, wherein the internal structure comprises at least one link rod for absorbing thrust attached to at least one point of an upstream portion of the internal structure and at least one point of a downstream portion of the internal structure in the vicinity of the pylon or optionally incorporated into the latter. 23. The nacelle as claimed in claim 22, wherein the link rod for absorbing thrust is oriented substantially in the structural alignment of the pylon. 24. The nacelle as claimed in claim 22, wherein the link rod for absorbing thrust has a fork attached to the internal structure at at least two points of the upstream portion of the internal structure, on either side of the horizontal mid-plane, the fork of the link rod having a junction point situated at a radial frame of the framework. 25. The nacelle as claimed in claim 1, wherein at least one portion of the framework elements comprising at least one of the radial frames, force-absorbing link rods, intermediate structure and longitudinal reinforcements, are fitted with a heat protection. 26. The nacelle as claimed in claim 1, wherein the internal structure has a one-piece framework. 27. The nacelle as claimed in claim 1, wherein the internal structure has a two-piece framework designed to be assembled substantially vertically. 28. A propulsion system, comprising a nacelle as claimed in claim 1, said nacelle accommodating a turbo-jet. 29. An aircraft, comprising at least one propulsion system as claimed in claim 28.
Manteiga John Alan ; Dykhuizen Cornelius Harm ; Joseph Thomas Peter ; Wilusz Christopher James ; Troup Robert Eugene ; Boger Ethan ; Franceschelli Anthony John, Link component for aircraft engine mounting systems.
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