US 11,679,889 B2
Nacelle of an aircraft propulsion assembly comprising a plurality of damper elements between a front section and a main section, and associated aircraft propulsion assembly
Clément Breton, Saint-Jean (FR); Julien Sentier, Colomiers (FR); Frédéric Vinches, Larra (FR); Alain Porte, Colomiers (FR); and Wolfgang Brochard, Carbonne (FR)
Assigned to Airbus Operations S.A.S.
Filed by Airbus Operations S.A.S., Toulouse (FR)
Filed on Jun. 13, 2019, as Appl. No. 16/440,214.
Claims priority of application No. 18 55835 (FR), filed on Jun. 28, 2018.
Prior Publication US 2020/0002016 A1, Jan. 2, 2020
Int. Cl. B64D 29/06 (2006.01); B64C 7/02 (2006.01); F01D 25/24 (2006.01)
CPC B64D 29/06 (2013.01) [B64C 7/02 (2013.01); F01D 25/243 (2013.01); F05D 2260/30 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A nacelle of an aircraft propulsion assembly, comprising:
a front section and a main section, said front section having a front end forming an air intake in the nacelle and a rear end comprising an annular stiffening frame around a rotary axis, said stiffening frame comprising an outer peripheral edge, connected to an outer panel of the nacelle, and an inner peripheral edge, said front section further comprising a connection part connecting said inner peripheral edge of the stiffening frame to an inner structure of the nacelle and a junction flange connected, via a plurality of connections, to said inner peripheral edge of the stiffening frame and to an engine flange of the main section,
wherein the junction flange comprises a plurality of deformable damper elements distributed along said inner peripheral edge of the stiffening frame.