Aircraft turbojet engine comprising two thrust reverser modules

A turbojet engine of an aircraft having a longitudinal direction and a transverse direction perpendicular to the longitudinal direction and comprising:

• a structure,
• two thrust reverser modules pivotably mounted on the structure between a close-together position and a spaced-apart position,
• wherein each thrust reverser module comprises an outer casing formed generally as a half-cylinder centered on the longitudinal direction, an inner casing formed generally as a half-cylinder centered on the longitudinal direction, housed inside the outer casing, and
• a securing system for securing, for each thrust reverser module, the inner casing to the outer casing, and comprising:
• a first hood secured between the inner casing and the outer casing of one of the reverser modules, and having a leading edge,
• a second hood secured between the inner casing and the outer casing of the other of the reverser modules,
• wherein a housing is formed between the first hood and the second hood and delimited by a securing wall of the first hood extending perpendicularly to the longitudinal direction at the rear of the leading edge,
• a seal comprising a foot and a sausage rigidly secured to the foot, wherein the foot is secured in the housing to the securing wall and wherein the sausage protrudes from the foot in the longitudinal direction, and
• a crushing means rigidly secured to the second hood and arranged to crush the sausage towards the securing wall when the second hood goes from the spaced-apart position to the close-together position.