ACOUSTIC FLOW STRAIGHTENER FOR TURBOJET ENGINE FAN CASING

The present invention relates to a structural or non-structural turbojet engine fan casing connecting arm ( 8 B) that also acts as a flow straightener downstream of the fan rotor ( 3 ). Its distinctive feature is that it is constructed in such a way as to form an acoustic attenuator. In particular,...

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Bibliographic Details
Main Authors MOREL PATRICK CHARLES GEORGES, RIOU GEORGES JEAN XAVIER, JULLIARD JACQUES MICHEL ALBERT, MOLINARI OLIVIER MICHAEL
Format Patent
LanguageEnglish
Published 02.10.2008
Subjects
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:The present invention relates to a structural or non-structural turbojet engine fan casing connecting arm ( 8 B) that also acts as a flow straightener downstream of the fan rotor ( 3 ). Its distinctive feature is that it is constructed in such a way as to form an acoustic attenuator. In particular, it comprises a closed cavity and perforations ( 83 ) on one of the faces ( 8 B in, 8 Bex) so as to form a Helmholtz resonator. The arm forms part of the intermediate casing ( 8 ).
Bibliography:Application Number: US20080019346