Thrust reverser provided with a lightweight thrust reverser flap
A thrust reverser includes a fixed structure and a movable structure defining an air stream, a flap including a single wall perforated on the surface thereof, and a structure strengthening the flap and having an acoustic function. The flap being articulated between the fixed structure and the movable structure to allow in a direct jet position, disposing the wall along an acoustic section of the movable structure and allowing the circulation of an air flow through the air stream, the acoustic section forming with the structure of the wall an acoustic resonator, and in a reverse jet position, disposing the wall to deflect an air flow passing through the air stream and allow the passage through the wall and through the air stream of a portion of the air flow deflected by the flap.
1. A thrust reverser of a turbojet engine nacelle for an aircraft, said thrust reverser comprising:
a fixed structure;
a movable structure cooperating with the fixed structure to delimit an air flow path; and
at least one thrust reverser flap comprising a single wall, said single wall being pierced on its surface so as to allow a passage through the at least one thrust reverser flap a portion of an air flow diverted by the at least one thrust reverser flap, said thrust reverser flap further comprising a stiffening structure connected to and extending away from the single wall to create open spaces, the single wall being exposed to air flow on both sides, and the stiffening structure stiffening the at least one thrust reverser flap and having an acoustic function, the at least one thrust reverser flap being articulated between the fixed structure and the movable structure to allow:
in a direct jet position, disposing said single wall of the at least one thrust reverser flap along an acoustic section of the movable structure so as to allow circulation of an air flow through the air flow path, said acoustic section forming with the movable structure of said single wall an acoustic resonator, and
in a reverse jet position, disposing said single wall of the at least one thrust reverser flap to divert an air flow passing through the air flow path and to allow the passage through the single wall of the at least one thrust reverser flap and through the air flow path a portion of the air flow diverted by the at least one thrust reverser flap.
2. The thrust reverser according to claim 1 , wherein the single wall of the at least one thrust reverser flap is dimensioned, in the direct jet position, to maintain between the movable structure and said acoustic section of the movable structure a predetermined clearance, the predetermined clearance is smaller than 3 millimeters.
3. The thrust reverser according to claim 2 , further comprising a spring maintaining said predetermined clearance between the at least one thrust reverser flap and said acoustic section of the movable structure.
4. The thrust reverser according to claim 3 , wherein a portion of the at least one thrust reverser flap is configured to receive the spring.
5. The thrust reverser according to claim 3 , wherein the single wall of the at least one thrust reverser flap has an opening provided for the passage of a deploying mechanism of the at least one thrust reverser flap for attachment thereof to the spring.
6. The thrust reverser according to claim 1 , wherein an edge of said single wall of the at least one thrust reverser flap facing the fixed structure in the direct jet position comprises a lip seal.
7. The thrust reverser according to claim 6 , wherein the lip seal is overmolded onto the edge of said single wall.
8. The thrust reverser according to claim 1 , wherein said single wall is made of aluminum, a thermoplastic material, composite fibers, or composite fibers in a matrix.
9. The thrust reverser according to claim 1 , wherein the stiffening structure forms a plurality of acoustic units.
10. A turbojet engine nacelle for an aircraft comprising a thrust reverser according to claim 1 .
11. A thrust reverser of a turbojet engine nacelle for an aircraft, said thrust reverser comprising:
a fixed structure;
a movable structure cooperating with the fixed structure to delimit an air flow path; and
at least one thrust reverser flap comprising a single wall, said single wall having a first surface facing the air flow path when the at least one thrust reverser flap is in a direct jet position and a second surface opposing the first surface, the single wall having pierced holes extending from the first surface to the second surface so as to allow a portion of an air flow diverted by the at least one thrust reverser flap to flow through the single wall, said thrust reverser flap further comprising a stiffening structure extending from the second surface away from the single wall and defining open spaces, both the first surface and the second surface of the single wall being exposed to air flow, and the stiffening structure performing a dual function of stiffening the at least one thrust reverser flap and having an acoustic function, the at least one thrust reverser flap being articulated between the fixed structure and the movable structure to allow:
in the direct jet position, disposing said single wall of the at least one thrust reverser flap along an acoustic section of the movable structure so as to allow circulation of an air flow through the air flow path, said acoustic section forming with said single wall an acoustic resonator, and
in a reverse jet position, disposing said single wall of the at least one thrust reverser flap to divert an air flow passing through the air flow path and to allow a portion of the air flow diverted by the at least one thrust reverser flap to pass through the single wall.
12. The thrust reverser according to claim 11 , wherein the first surface and the second surface define a thickness of the single wall.