Cooling passages for airfoil leading edge

Details Cooling passages for airfoil leading edge Cooling passages for airfoil leading edge

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01)

Patent

CA 2268915

A cooling structure for the leading edge area of an airfoil having a plurality of passages wherein each passage has a radial component and a downstream component relative to the leading edge axis, and the outlet of each passage has a diffuser area formed by conical machining, wherein the diffuser area is recessed in the wall portion downstream of the passage.

L'invention porte sur une structure de refroidissement de la surface du bord d'attaque d'un profil aérodynamique, qui est munie d'une pluralité de passages présentant chacun une composante radiale et une composante aval par rapport à l'axe du bord d'attaque. La sortie de chacun des passages présente une zone de diffusion usinée en cône, et en retrait dans la partie de la paroi en aval du passage.

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