US 11,667,387 B2
Ice protection and boundary layer suction system for an aircraft aerofoil
Said Elmouden, Mons (BE); and Nicolas Dellisse, Burdinne (BE)
Assigned to SONACA S.A., Gosselies (BE)
Appl. No. 17/419,515
Filed by SONACA S.A., Gosselies (BE)
PCT Filed Sep. 23, 2020, PCT No. PCT/EP2020/076562
§ 371(c)(1), (2) Date Jun. 29, 2021,
PCT Pub. No. WO2021/058560, PCT Pub. Date Apr. 1, 2021.
Claims priority of application No. 2019/5628 (BE), filed on Sep. 24, 2019.
Prior Publication US 2022/0212805 A1, Jul. 7, 2022
Int. Cl. B64C 21/06 (2023.01); B64C 3/14 (2006.01); B64C 21/04 (2023.01); B64D 15/04 (2006.01)
CPC B64D 15/04 (2013.01) [B64C 21/06 (2013.01); B64C 3/14 (2013.01); B64C 21/04 (2013.01); B64C 2230/04 (2013.01); B64C 2230/06 (2013.01); B64C 2230/20 (2013.01); B64C 2230/22 (2013.01)] 7 Claims
OG exemplary drawing
 
1. Boundary layer suction and ice protection system for an aircraft aerofoil, including a wall provided with micro-perforations and delimiting a leading edge extended by a lower surface wall and by an upper surface wall, with an inner wall linking the upper surface wall to the lower surface wall and delimiting with the leading edge a front bay, this system including a perforated tube running along the leading edge by extending into the front bay, a check valve coupled to the tube to allow the intake of air into the tube through the check valve and to prohibit the backflow of air coming from the tube through the check valve, means for sucking the air from this tube in order to suck the boundary layer successively via the micro-perforations of the wall and the perforations of the tube, and means for blowing hot air into this perforated tube during the ice protection phase, this hot air being evacuated successively via the perforations of the tube and the micro-perforations of the wall.