US 11,746,706 B2
Air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element, and a nacelle element
Bruno Alexandre Didier Jacon, Moissy-Cramayel (FR); Baghdad Achbari, Moissy-Cramayel (FR); Faouzi Aliouat, Moissy-Cramayel (FR); and Hervé Simonotti, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/299,963
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Nov. 19, 2019, PCT No. PCT/FR2019/052744
§ 371(c)(1), (2) Date Jun. 4, 2021,
PCT Pub. No. WO2020/115383, PCT Pub. Date Jun. 11, 2020.
Claims priority of application No. 1872399 (FR), filed on Dec. 5, 2018.
Prior Publication US 2021/0332762 A1, Oct. 28, 2021
Int. Cl. F02C 7/28 (2006.01); F16J 15/06 (2006.01); F01D 11/00 (2006.01); F01D 25/26 (2006.01); F16J 15/02 (2006.01)
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
OG exemplary drawing
 
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.