| 摘要 |
The invention relates to a nacelle (12) for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis (X) is mounted, the nacelle including a wall (24) concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct (26) for the fluid inner flow, comprising at the downstream end (26a) of said nacelle wall a passage section of the flow outlet, characterised in that the nacelle includes displacement means (42) for displacing on request a portion (24b) of the nacelle wall in order to modify the passage section of the flow outlet through which a major portion of the flow (Fi') escapes, said displacement forming in the nacelle wall at least one opening (28; 53) through which a small portion of the flow, called the leak flow (Fi '), naturally escapes, the nacelle further comprising a fluid device (30; 54) that uses a fluid for compelling the leak flow to flow along the outer face (24e) of the portion of the nacelle wall located downstream relative to said at least one opening. |
