CPC F02C 7/28 (2013.01) [F01D 11/003 (2013.01); F01D 11/005 (2013.01); F01D 25/265 (2013.01); F16J 15/027 (2013.01); F16J 15/061 (2013.01); F05D 2220/323 (2013.01); F05D 2240/55 (2013.01); F05D 2250/291 (2013.01); F05D 2300/437 (2013.01); F05D 2300/614 (2013.01)] | 12 Claims |
1. An air-sealing device adapted to be inserted between an aircraft dual-flow turbine engine casing element and a nacelle element, the sealing device comprising a fixing tab at an end of which there is a sealing portion having an outer surface adapted to be contacted by the casing element and the nacelle element, and an inner surface delimiting a hollow,
wherein the inner surface defines two opposite protuberances, extending inside the hollow towards each other, and in that in cross section of the sealing device, each protuberance defines a protuberance height direction arranged to form an angle comprised between 40° and 60° with a longitudinal direction of the fixing tab.
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