Jet engine nacelle for an aircraft and aircraft comprising such a nacelle

Abstract

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 atThe 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 atleast 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 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 outhe 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 flotlet 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 waw (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.ll located downstream relative to said at least one opening.

Description

technical field [0001] The invention relates to an aircraft jet nacelle equipped with a variable nozzle system. Background technique [0002] The variable nozzle system was originally developed for military aviation. [0003] These systems can greatly improve the thermodynamic performance of the turbine. [0004] Traditionally, turbines installed on airliners have not been equipped with variable nozzle systems. [0005] In fact, conventional variable nozzle systems lead to very important dimensional constraints, which are directly related to the circumference of the nozzle, whose section must be varied. [0006] However, airliner equipped turbines are characterized by high bypass ratios of essentially 4 to 8, which result in larger nozzle diameters. [0007] It is therefore unacceptable to install a conventional variable nozzle system on an airliner, risking considerably increasing the complexity and mass of the jet nacelle, detrimental to the aerodynamic performance of t...

AI Technical Summary

Problems solved by technology

[0007] Therefore, installing a conventional variable nozzle system on an airliner risks greatly increasing the complexity and mass of the jet nacelle, detrimental to the aerodynamic performance of the propulsion plant, which is unacceptable

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