Nacelle for aircraft engine having a nozzle with a variable section
The invention relates to a nacelle for an aircraft engine that comprises a front cowling ( 13 ) and a rear cowling ( 1 a ), the rear cowling ( 1 a ) being mounted so as to slide between an upstream position defining a reduced nozzle ( 9 ) section and a downstream position defining an enlarged nozzle ( 9 ) section. The nacelle includes an intermediate member ( 25 ) arranged edge-to-edge with said front cowling ( 13 ), said member defining a housing ( 27 ) for receiving the upstream edge ( 11 ) of said rear cowling ( 1 a ) when the latter is in the upstream position.
1. A nacelle for an airplane engine, comprising:
a thrust reverser;
a front cowl and a rear cowl, the rear cowl being mounted such that it can the rear cowl can slide between an upstream position defining a small cross section of nozzle and a downstream position defining an enlarged cross section of nozzle; and
an intermediate member attached to a front frame of the thrust reverser and positioned edge to edge with said front cowl, this intermediate member; defining a housing having a hollow interior facing downstream into which an upstream edge of said rear cowl penetrates when the rear cowl is in its upstream position and a centering member extending upstream and on opposite side of the housing for proper positioning of the front cowl.
2. The nacelle as claimed in claim 1 , wherein said front cowl has reinforcements situated just upstream of said centering member.
3. The nacelle as claimed in claim 1 , wherein said front cowl comprises reinforcements situated in line with said centering member, said centering member being offset radially inward by a distance that corresponds substantially to a combined radial thickness of said front cowl and of said reinforcements.
4. The nacelle as claimed in claim 1 , wherein said housing comprises a radially inner edge defining a slope for the upstream edge of said rear cowl.
5. The nacelle as claimed in claim 1 , wherein said housing has a radially outer edge defining a slope for the upstream edge of said rear cowl.
6. The nacelle as claimed in one of claim 4 , further comprising a seal adjacent to said slope.
7. The nacelle as claimed in claim 4 , wherein said rear cowl comprises, on an interior face, reinforcements positioned near the upstream edge.
8. The nacelle as claimed in claim 1 , wherein a line where said front cowl meets said intermediate member is contained in a plane not perpendicular to an axis of said nacelle.
9. The nacelle as claimed in claim 1 , wherein said intermediate member can be attached to a fan casing of said engine.
10. The nacelle as claimed in claim 1 , wherein said intermediate member comprises two halves that can be mounted in an articulated manner on a support pylon for said engine.
11. The nacelle as claimed in claim 1 , wherein said intermediate member forms part of a cowl of a fan of said engine.
12. The nacelle as claimed in claim 1 , further comprising a cascade-type thrust reverser with cascades of vanes an exterior part of which forms said rear cowl.
13. The nacelle as claimed in claim 12 , wherein said thrust reverser comprises, in addition to said exterior part, an interior part able to move independently of said exterior part.
14. The nacelle as claimed in claim 12 , wherein said intermediate member forms an integral part of a fixed structure of said thrust reverser.
15. The nacelle as claimed in claim 1 , wherein said front cowl incorporates an air intake lip of this nacelle.
16. The nacelle as claimed in claim 1 , wherein said front cowl can be mounted such that said front cowl can slide on said engine.