Ring of turbojet vanes including an acoustic treatment structure

Number of patents in Portfolio can not be more than 2000

United States of America Patent

PATENT NO 10723476
APP PUB NO 20190152618A1
SERIAL NO

16185257

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Importance

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Abstract

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A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.

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Patent Owner(s)

Patent OwnerAddress
SAFRAN AIRCRAFT ENGINES75015 PARIS

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Mardjono, Jacky Novi Nogent sur marne, FR 21 133
Marlin, Francois Marie Paul Villiers sous Grez, FR 13 159
Papin, Thierry Georges Paul Varennes-Jarcy, FR 25 117
Perdrigeon, Christophe Marcel Lucien Ballainvilliers, FR 19 57
Zaccardi, Cedric Saint Maur des Fosses, FR 10 58

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