FIELD: turbine engines.
SUBSTANCE: invention relates to an airtight sealing device (40) configured to be inserted between the element (16) of the body of a double-flow turbine engine of an aircraft and the element (30) of the nacelle. The sealing device contains a fastening tab (42), at the end of which there is a sealing section (44) having an outer surface made with the possibility of contact with the body element and the gondola element, and an inner surface limiting the cavity. The inner surface defines at least one bulge extending into the interior of the cavity.
EFFECT: invention has a sufficiently high rigidity in operation to withstand air pressure, regardless of the level of deformation of the sealing device.
8 cl, 8 dwg
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