CPC B64D 29/06 (2013.01) [B64C 7/02 (2013.01); F01D 25/243 (2013.01); F05D 2260/30 (2013.01)] | 15 Claims |
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.
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