Sealing joint for aircraft turbojet engine nacelle
A sealing joint for an aircraft turbojet engine nacelle includes a bead designed to be mounted in a joint support. The sealing joint is characterized in that the bead includes a retaining projection which extends in a direction substantially transverse to a longitudinal axis of the sealing joint, the retaining projection being designed to extend through the joint support when the sealing joint is mounted in the support thereof and/or a sealing lip which extends under the bead in a direction substantially parallel to the longitudinal axis of the sealing joint and which is designed to be compressed on the joint support when the sealing joint is mounted in the support thereof.
1. A seal for an aircraft turbojet engine nacelle, said seal comprising a bead intended to be mounted in a seal support, wherein said bead comprises:
a plurality of retaining protrusions spaced apart from each other, extending in a direction substantially transverse to a longitudinal axis of said seal, said plurality of retaining protrusions being configured to pass through said seal support when said seal is mounted in the seal support thereof, and/or
a sealing lip extending below said bead, in a direction substantially parallel to said longitudinal axis of said seal, configured to be compressed on the seal support when said seal is mounted in the seal support thereof.
2. The seal according to claim 1 , wherein the plurality of retaining protrusions are regularly spaced apart from each other.
3. The seal according to claim 1 , wherein the plurality of retaining protrusions are not regularly spaced apart from each other.
4. The seal according to claim 1 , wherein the plurality of retaining protrusions are distributed in a staggered manner relative to the longitudinal axis of the seal.
5. The seal according to claim 1 , wherein at least one of the plurality of retaining protrusions has a thickness less than or greater than or equal to the thickness of the bead of the seal.
6. The seal according to claim 1 , wherein at least one of the plurality of retaining protrusions includes a circumferential groove.
7. The seal according to claim 1 , wherein the sealing lip extends over a length less than or equal to the length of the bead of the seal.
8. The seal according to claim 7 , wherein the sealing lip extends continuously over the length.
9. The seal according to claim 7 , wherein the sealing lip extends discontinuously over the length.
10. A sealing assembly comprising:
a seal according to claim 1 ; and
a seal support in which the bead of said seal is mounted, wherein the seal support comprises retaining orifices through which the plurality of retaining protrusions of said seal passes and in that the sealing lip of said seal is compressed on said seal support.
11. A propulsion unit for an aircraft, the propulsion unit comprising:
a turbojet engine; and
a nacelle supporting said turbojet engine, said nacelle comprises a cascade thrust reverser device comprising a cowl, wherein the cowl is movable between a retracted position providing an aerodynamic continuity of the nacelle for an operation of the nacelle in direct jet mode and between a deployed position defining an annular passage in the nacelle for an operation of the nacelle in reverse jet mode, wherein said propulsion unit comprises a sealing assembly according to claim 10 , wherein the seal comprises a sealing body supported by the bead of said seal, said sealing body being in contact with a deflection edge of the turbojet engine.
12. A method for dismounting a sealing assembly defined according to claim 10 , wherein the method comprises a step of cutting the plurality of retaining protrusions at a portion thereof which passes through the one or more retaining orifices of the seal, then removing the seal from the seal support.