AIR INLET FOR A TURBOFAN ENGINE

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).

Description

BRIEF DESCRIPTION OF THE DRAWINGS

An embodiment, which does not limit the invention, will be described with reference to the drawings, in which

FIG. 1 is a side view showing the front part of a jet engine nacelle;

FIG. 2 is a side view, from the outer side, showing the front part of a jet engine nacelle according to the invention;

FIG. 3 is a plan view showing the nacelle of FIG. 2 mounted below an aircraft wing;

FIG. 4 is a side view, from the outer side, showing the front part of a jet engine nacelle according to the invention wherein the leading edge is not planar.

Claims

1. 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.

2. The air inlet as claimed in claim 1, in which the leading edge of the upper part is to the rear with respect to the leading edge of the lower part.

3. 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.

4. 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°.

5. The air inlet as claimed in claim 3 or 4, in which said plane is inclined with respect to a horizontal line perpendicular to the axis XX of the engine by an angle A2 of between 0° and 15°, excluding 0°.

6. The air inlet as claimed in claims 1 and 2, in which the leading edge forms a scoop surface or a surface of complex shape.

7. A turbofan engine in which the air inlet of the nacelle is configured as claimed in one of claims 1 to 6.