AIRCRAFT REJECTION THRUST REVERSING GRILLE

Abstract

Thrust reverser grid (10) comprising: - spars each extending along a longitudinal direction (X) and a direction (Z), called the height, and spaced from each other along a transverse direction, each spar having two large opposing faces (12.1), - blades (14.1, 14.2) each extending transversely between two facing spars and spaced from each other along the longitudinal direction (X), each large face (12.1) of each spar having, between two consecutive blades (14.1, 14.2), two subsurfaces (SS1, SS2) offset longitudinally and forming an angle of less than 90° between them in a plane, the two subsurfaces (SS1, SS2) being connected to each other by a third subsurface (SS3) which has, in a plane (XZ), a triangular shape with a vertex (S) in the lower part of the a longeron and a base (B) in the upper part and which is offset longitudinally with respect to the apex (S).Figure for the abridged version: Fig.3.

Claims

Claims

1. A thrust reverser grid for an aircraft jet engine, comprising: - a plurality of spars (12) each extending in a longitudinal direction (X) and which are spaced from each other in a transverse direction (Y), each spar also extending in a direction (Z), called height, which is perpendicular to the longitudinal (X) and transverse (Y) directions, each spar having two large opposite faces (12.1, 12.2), - a plurality of blades (14, 14.1, 14.2) each extending between the spars (12) in the transverse direction (Y), the blades arranged between two spars facing each other being spaced from each other in the longitudinal direction (X), each of the two large opposite faces (12.1, 12.2) of each spar (12) having, between two consecutive blades (14.1, 14.2) spaced along the longitudinal direction (X) and each connected to the relevant large face of the spar, two sub-surfaces (SS1, SS2) which are longitudinally offset from each other along the longitudinal axis (X), the two sub-surfaces forming between them, according to a projection view in a plane (XY), a non-zero angle α less than 90°, the two sub-surfaces (SS1, SS2) being connected to each other by a third sub-surface (SS3) which has, according to a projection view in a plane (XZ), a general triangle shape having a vertex (S) positioned in the lower part of the spar and a base (B) positioned in the upper part of the spar and which is longitudinally offset from the position of the vertex (S).

2. Thrust reverser grid according to claim 1, in which, according to a projection view in a plane (XY), the two sub-surfaces (SS1, SS2) form between them a non-zero angle of less than 10°, preferably less than 5°.

3. Thrust reverser grid according to claim 1 or 2, in which each spar (12) comprises two opposite longitudinal edges (12.3, 12.4) which each connect the two opposite large faces (12.1, 12.2) of the spar to each other, the base (B) of the general triangular shape of the third sub-surface (SS3) of each large face of the spar being positioned, according to a projection view in a plane (XZ), on the longitudinal edge, called the upper edge (12.3), which is in the upper part of the spar.

4. Thrust reverser grid according to claim 3, in which the apex (S) of the general triangular shape is located, according to a projection view in a plane (XZ), at a distance from the opposite longitudinal edge, called the lower edge (12.4) of the spar.

5. Thrust reverser grid according to the preceding claim, in which the general triangular shape of the third sub-surface (SS3) of each large face (12.1, 12.2) of the spar comprises, according to a projection view in a plane (XZ), a side (Cl) of the triangle which is adjacent to the second sub-surface (SS2) and which is inclined relative to the lower edge (12.4) of the spar at an angle [3 which is between 10 and 80°, preferably between 30 and 70°.

6. A thrust reverser grid according to claim 5, wherein the general triangular shape of the third sub-surface (SS3) of each large face (12.1, 12.2) of the spar comprises, in a projection view in a plane (XZ), another side (C2) of the triangle which is adjacent to the first sub-surface (SS1) and which is inclined relative to the lower edge (12.4) of the spar at an angle greater than the angle [3 and which is less than or equal to 90°.

7. Thrust reverser grid according to one of the preceding claims, in which the third sub-surface (SS3) of each large face (12.1, 12.2) of each spar is planar, according to a projection view in a plane (XY).

8. Thrust reverser grid according to one of claims 1 to 6, in which the third sub-surface (SS3) of each large face (12.1, 12.2) of each spar is convex, according to a projection view in a plane (XY).

9. Thrust reverser grid according to one of the preceding claims, in which the two consecutive blades (14.1, 14.2) spaced apart in the longitudinal direction (X) define between them a cavity (C) capable of being traversed by an air flow, a first blade (14.1) comprising an extrados-forming surface (Sel) oriented towards the cavity, while the second blade (14.2) comprises an intrados-forming surface (Si2) oriented towards the cavity, a first (SS1) of the two sub-surfaces (SS1, SS2) of the large face concerned of the spar being adjacent to the first blade (14.1), while the second sub-surface (SS2) is adjacent to the second blade (14.2).

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