Air inlet for a turbofan engine
AssigneeSnecma
InventorsPhilippe Gerard CHANEZ, Pierre Philippe Marie Loheac
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Abstract
The present invention relates to an air inlet for a nacelle of a jet engine with a front fan, comprising an upper part (115S), a lower part (115I), an inner lateral part (115int) and an outer lateral part (ext), defining a leading edge (115) between an external wall (111) of the nacelle and an internal wall (113) forming the air supply channel of the jet engine. According to the invention, the air inlet is characterized in that the leading edge of the outer lateral part (115ext) is to the rear with respect to the leading edge of the inner lateral part (115int). Preferably, the leading edge of the upper part (115S) is likewise to the rear with respect to the leading edge of the lower part (115I).
Claims7
An air inlet for a nacelle of a jet engine with a front fan, comprising an upper part, a lower part, an inner lateral part and an outer lateral part, together defining a leading edge between an external wall of the nacelle and an internal wall forming the air supply channel of the jet engine, wherein the leading edge of the outer lateral part is to the rear with respect to the leading edge of the inner lateral part.
The air inlet as claimed in the preceding claim, in which the leading edge forms a plane, the plane being inclined with respect to the axis of the engine.
The air inlet as claimed in the preceding claim, in which said plane is inclined with respect to the vertical by an angle A1 of between 0° and 15°.
Dependencies are inferred from the claim text.