ACOUSTIC TREATMENT DEVICE FOR AN AIRCRAFT TURBOJET ENGINE NACELLE

• US 20200135160A1
• Filed: 12/23/2019
• Published: 04/30/2020
• Est. Priority Date: 06/23/2017
• Status: Active Grant

• Current Assignee: Safran Nacelles
• Original Assignee: Safran Nacelles
• Inventors: CAZUC, Xavier, DEHEZ, MERIL, HAMEL, LAURE, THISSE, ERIC
• Granted Patent: US 11,735,153 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 2033/0206 comprising noise reduction means, e.g. acoustic liners
• CPC Class Codes: B64D 2033/0273 for jet engines
• CPC Class Codes: B64D 2033/0286 for turbofan engines
• CPC Class Codes: B64D 29/00 Power-plant nacelles, fairings, or cowlings nacelles not otherwise provided for B64C
• CPC Class Codes: B64D 33/02 of combustion air intakes air intakes for gas-turbine plants or jet-propulsion plants per se F02C7/04; air intakes for combustion engines in general F02M35/00
• CPC Class Codes: F02C 7/045 having provisions for noise suppression
• CPC Class Codes: F02C 7/24 Heat or noise insulation air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00
• CPC Class Codes: G10K 11/162 Selection of materials
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An acoustic treatment device for an aircraft turbojet engine nacelle forms an annular ring including several sections, each section having a sound absorption structure, an outer skin and two lateral skins attached to the inner air inlet shroud of such a nacelle by fasteners, and the sections being connected to each other by battens.

Claims

1. An acoustic treatment device for an inner shroud of an air inlet of an aircraft turbojet engine nacelle, the acoustic treatment device comprising;

an acoustic absorption structure;

an outer skin fastened on an outer surface of the acoustic absorption structure;

two lateral skins clasping the acoustic absorption structure, each lateral skin comprising a fastening foot; and

fasteners, each fastening foot receiving a portion of the fasteners, wherein;

the acoustic treatment device forms an annular crown mounted on an external periphery of the inner shroud to absorb acoustic energy originating from the inner shroud or a part connected to the inner shroud,

the acoustic treatment device fastened to the inner shroud by the fasteners, and

the annular crown comprising a plurality of segments, each segment comprising the acoustic absorption structure, the outer skin and the two lateral skins, the plurality of segments connected to each other by battens.

2. The device according to claim 1, wherein the annular crown comprises six segments.

3. The device according to claim 1, wherein the two lateral skins are not fastened to the acoustic absorption structure.

4. An inner shroud of an air inlet of an aircraft turbojet engine nacelle comprising an acoustic treatment device according to claim 1.