Gas ejection cone for an aircraft turbojet equipped with a...

F - Mech Eng,Light,Heat,Weapons – 02 – K

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F02K 3/06 (2006.01) F02K 1/08 (2006.01)

Patent

CA 2696178

The present invention relates to a gas ejection cone (8) for an aircraft turbojet, the cone having a hollow main body (30) defining, on the outside, a radially inner skin (36) of an annular primary flow channel. According to the invention, it further includes a device (34) for generating turbulence in the primary flow, limiting jet noise, which is mounted so as to move on the main body so as to be able to be displaced from an extracted position in which it projects towards the downstream relative to a downstream end of the hollow main body and a retracted position in which it is retracted into its hollow main body, and vice versa. In addition, the device (34) includes a cylindrical support body (42) having an axis parallel to an axis (32) of the ejection cone, and also at least one fin (46) supported by the body (42).

La présente invention se rapporte à un cône d'éjection des gaz (8) pour turboréacteur d'aéronef, le cône présentant un corps principal creux (30) définissant extérieurement une peau radialement intérieure (36) d'un canal annulaire de flux primaire. Selon l'invention, il comprend en outre un dispositif (34) de génération de turbulences de flux primaire limitant le bruit de jet, monté mobile sur le corps principal de manière à pouvoir être déplacé d'une position extraite dans laquelle il est en saillie vers l'aval par rapport à une extrémité aval du corps principal creux, et une position rétractée dans laquelle il est escamoté dans ce corps principal creux, et inversement. De plus, le dispositif (34) comprend un corps cylindrique de support (42) d'axe parallèle à un axe (32) du cône d'éjection, ainsi qu'au moins une ailette (46) supportée par le corps (42).

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