ACOUSTIC SPLITTER FOR TURBOJET FAN CASE

The present invention pertains to a linking arm (8B), structural or not, of a turbojet fan casing, also forming a flow rectifier downstream from the fan rotor (3). It is characterised by the fact that it is made so as to form an acoustic damper. In particular, it includes a closed cavity and perfora...

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Bibliographic Details
Main Authors RIOU, GEORGES JEAN XAVIER, MOREL, PATRICK CHARLES GEORGES, MOLINARI, OLIVIER MICHAEL, JULLIARD, JACQUES MICHEL ALBERT
Format Patent
LanguageEnglish
French
Published 26.08.2014
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:The present invention pertains to a linking arm (8B), structural or not, of a turbojet fan casing, also forming a flow rectifier downstream from the fan rotor (3). It is characterised by the fact that it is made so as to form an acoustic damper. In particular, it includes a closed cavity and perforations (83) on one of the faces (8Bin, 8Bex) so as to provide a Helmholtz resonator. The arm is a part of the intermediate casing (8). La présente invention porte sur un bras de liaison (8B), structural ou non, de carter de soufflante de turboréacteur formant également redresseur de flux en aval du rotor de soufflante (3). Il est caractérisé par le fait qu'il est constitué de manière à former amortisseur acoustique. En particulier il comprend une cavité fermée et des perforations (83) sur l'une des faces (8Bin, 8Bex) de manière à constituer un résonateur de Helmholtz. Le bras fait partie du carter intermédiaire (8).
Bibliography:Application Number: CA20082619315