Turbojet engine nacelle with translatable upstream cowl
Turbojet engine nacelle ( 1 ) comprising an air intake structure ( 4 ) able to channel a flow of air towards a fan of the turbojet engine, and a central structure ( 5 ) intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel ( 40 ) incorporating an air intake lip ( 4 a ) and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle ( 1 ), and a maintenance position in which the outer panel ( 40 ) is set away from the outer structure of the central section and the air intake lip ( 4 a ) is set away from the inner panel of the air intake structure, characterized in that the longitudinal outer panel ( 40 ) is associated with guide means of the rails ( 15 )/slide ( 16 ) type, at least part of said guide means being positioned as close as possible to an interface with a pylon ( 2 ) to which the nacelle is attached.
1. A turbojet engine nacelle comprising:
an air intake structure able to channel a flow of air towards a fan of the turbojet engine; and
a central structure surrounding said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising a casing surrounding the fan and an outer structure,
wherein the air intake structure comprises an inner panel and a longitudinal outer panel incorporating an air intake lip, and the longitudinal outer panel extends so far as to incorporate at least part of the outer structure of the central section and beyond, the longitudinal outer panel being translationally mobile between an operating position and a maintenance position, the operation position in which the longitudinal outer panel ensures the aerodynamic continuity of the outside of the nacelle, and the maintenance position in which the longitudinal outer panel is set away from the outer structure of the central section and the air intake lip is set away from the inner panel of the air intake structure, and
wherein the longitudinal outer panel has a cutout bypassing a pylon in the operating position and the cutout forms an interface with the pylon to which the nacelle attached, and the longitudinal outer panel being associated with structural guide means comprising rails and slides, said rails and slides being arranged near the interface, and wherein the longitudinal outer panel is equipped with at least one centering means arranged on an opposite side of the pylon, and a space between at least two rails of the guide means is maintained via at least one fitting arranged between unsupported upstream ends of said at least two rails and fastened in each of said rails the unsupported upstream ends of the rails being cantilevered relative to the pylon so as to be not directly supported by the pylon.
2. The nacelle according to claim 1 , wherein the interface with the pylon comprises sealing means.
3. The nacelle according to claim 2 , wherein the sealing means are arranged so as to have a slope releasing the crushing of the joint during opening and closing manipulations of the longitudinal outer panel.
4. The nacelle according to claim 1 , wherein said at least two rails of the guide means are associated with said at least one centering means.
5. The nacelle according to claim 1 , wherein at least one rail is equipped, at an upstream portion of said rail, with a reinforcing connecting rod connected to the pylon.
6. The nacelle according to claim 1 , wherein said at least one centering means comprise at least one distortion limiter including at least one fitting mounted on a stationary structure or the longitudinal outer panel so as to come between two fittings mounted on the longitudinal outer panel or the stationary structure, a space being formed when the longitudinal outer panel is in the closed position between the fitting mounted on the stationary structure and the fittings mounted on the longitudinal outer panel.
7. The nacelle according to claim 1 , wherein the structural guide means are associated with additional means for reacting forces arranged near the interface, and able to cooperate with additional force reacting means of a stationary element.
8. The nacelle according to claim 7 , wherein the additional means for reacting forces are shearing pins and the stationary element is the pylon.
9. The nacelle according to claim 1 , wherein at least part of the structural guide means is contained in a longitudinal enclosure of the central structure.
10. The nacelle according to claim 1 , wherein at least part of the structural guide means has an overhang downstream of the rails or slides at an area of a rear section of the nacelle.
11. The nacelle according to claim 1 , wherein the nacelle is a nacelle for an aircraft fuselage.
12. The nacelle according to claim 1 , wherein the nacelle is fastened to a substantially horizontal pylon.
13. The nacelle according to claim 1 , wherein said at least one centering means comprise at least one distortion limiter including at least one fitting mounted on a stationary structure or the longitudinal outer panel so as to come between two fittings mounted on the mobile structure or the stationary structure, a space being formed when the longitudinal outer panel is in the closed position between the fitting mounted on the longitudinal outer panel and the fittings mounted on the stationary structure.