US 11,807,379 B2
Turbofan engine, nacelle thereof, and associated method of operation
Philippe-André Tetrault, Boucherville (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jan. 28, 2020, as Appl. No. 16/774,778.
Application 16/774,778 is a continuation of application No. 16/699,001, filed on Nov. 28, 2019, abandoned.
Prior Publication US 2021/0163146 A1, Jun. 3, 2021
Int. Cl. B64D 33/02 (2006.01); B64D 15/04 (2006.01); F02C 6/08 (2006.01); F02C 7/047 (2006.01); F02K 3/06 (2006.01)
CPC B64D 33/02 (2013.01) [B64D 15/04 (2013.01); F02C 6/08 (2013.01); B64D 2033/0206 (2013.01); B64D 2033/0233 (2013.01); B64D 2033/0286 (2013.01); F02C 7/047 (2013.01); F02K 3/06 (2013.01); F05D 2220/323 (2013.01); F05D 2220/36 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbofan engine nacelle, the nacelle comprising an inlet portion having a duct wall and an outer skin, the duct wall being annular around a central axis and having a surface forming a radially-outer delimitation to a gas path upstream of a fan area, the duct wall extending from a rounded inlet edge of the nacelle to the fan area, a cavity located inside the inlet portion, a compressed air inlet leading into the cavity, and an outlet fluidly connecting the cavity to the gas path, the outlet having a plurality of apertures disposed circumferentially around the duct wall, the apertures sloping circumferentially at an inner face of the duct wall, each of the apertures extending from an aperture inlet to an aperture outlet, the aperture outlet directed circumferentially and axially relative to the central axis.