Acoustic management, on a turbomachine or a nacelle

A method for the preparation of a support area and for acoustic management:

• the support area being located on an aircraft turbomachine (3,12) comprising an air inlet cone (26), or
• the support area being located on a nacelle (1,10) of such a turbomachine (3,12), the turbomachine comprising:
• an outer structure (1a) comprising at least one outer annular casing (17), and possibly:
• an inner structure (1b) comprising a fairing (15) of a turbojet (3) engine (3,12,19), which turbojet engine (3,12,19) having an air inlet cone (26) comprises a fan (11), the inner structure of the nacelle (1b) then defining, with the outer structure (1a), an annular air vein (21) for secondary air, and
• an exhaust nozzle (39) comprising an outer primary nozzle sleeve (41) and an inner primary nozzle tip (43) defining between them an outlet channel for a primary air flow (45) exciting the turbojet engine (3,12,19),
• in which method:
• on said support area of the aircraft turbomachine (3,12) or of the nacelle (1,10) is reserved a recess (34) recessed with respect to a surrounding general surface (36) of said support area defining a surface for contact with moving air (21,28,45):
• located in the aircraft turbomachine (3,12), on the air inlet cone (26), or
• located on the nacelle (1,10),
• the recess (34) being adapted to removably receive an acoustic panel (30) and a non-acoustic panel (32), each having a surface for contact with moving air (21,28,45), one in replacement of the other,
• depending on an acoustic or an aerodynamic criterion, one of said acoustic panel and non-acoustic panel is removed from the recess (34) in which said one of the acoustic panel and non-acoustic panel was contained and is replaced by a replacement panel (30,32) adapted to replace said one of the acoustic panel and non-acoustic panel and which has a surface for contact with moving air (21,28,45), said replacement panel being an acoustic panel (30) if the panel (32) removed is non-acoustic, and vice versa.

An acoustic management assembly,

• the acoustic management assembly comprising an area (60) of a support (38):
• the support area being located on an aircraft turbomachine (3,12) comprising an air inlet cone (26), or
• the support area being located on a nacelle (1,10) of a turbomachine (3, 12), the turbomachine comprising:
• an outer structure (1a,33a) comprising at least one outer annular casing (17,33a . . . ), and possibly:
• an inner structure (1b) comprising a fairing (15) of a turbojet engine (3,12,19), which turbojet engine comprises a fan (11) comprising an air inlet cone (26), the inner structure (1b) defining, with the outer structure (1a), an annular air vein (21a) of a secondary air, and
• an exhaust nozzle (39) comprising an outer primary nozzle sleeve (41) and an inner primary nozzle tip (43) defining between them an outlet channel for a primary air flow (45) exiting the turbojet engine, and
• the acoustic management assembly further comprising a first panel (30,32),
• wherein:
• on said area of the aircraft turbomachine (3,12) or of the nacelle (1,10) is reserved a recess (34) recessed with respect to a surrounding general surface (36) of said area defining a surface for contact with moving air (21,28,45):
• in the aircraft turbomachine (3,12), on the air inlet cone (26), or
• on the nacelle (1,10),
• the recess (34) is adapted to receive said first panel (30,32), which has a surface for contact with moving air (21,28,45),
• the support (38) and/or said first panel (30,32) comprise removable connecting elements (58) for, in the recess (34), removably mounting said first panel with respect to the support, and
• said first panel (30,32) is an acoustic panel or a non-acoustic panel, and the assembly further comprises a second panel (32,30):
• which is an acoustic panel (30) if the first panel (32) is non-acoustic, and vice-versa, and
• which, together with the support (38), is adapted to be received in the recess (34), instead of the first panel (30,32).