Porous metal bodies used for attenuating aviation turbine noise

Details Porous metal bodies used for attenuating aviation turbine noise Porous metal bodies used for attenuating aviation turbine noise

G - Physics

10

K

G10K 11/16 (2006.01)

Patent

CA 2634548

A structural element used for attenuating aviation turbine noise is provided with pores (1, 2) embodied in the form of cylindrical channels which are open on the first ends inside the turbine housing and closed on the opposite ends thereof, wherein the diameter (D) of each channel ranges approximately from 0.1 to 0.3 mm, each channel is remote at least along one part of the length thereof from the closest neighbours at a minimum distance ranging approximately from 0.02 to 0.3 mm and the ration between the channel length and diameter thereof is of the order of 102.

Élément structural propre à atténuer le bruit d'une turbine aéronautique, présentant des pores (1, 2) sous la forme de canaux cylindriques débouchant par une première de leurs extrémités à l'intérieur du carter de la turbine et fermés à leur extrémité opposée, chaque canal ayant un diamètre (D) compris entre 0,1 et 0,3 mm environ et étant situé, sur une partie au moins de sa longueur, à une distance minimale (e) de ses plus proches voisins comprise entre 0,02 et 0,3 mm environ, et le rapport entre la longueur et le diamètre des canaux étant de l'ordre de 102.

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