Cooled turbine vane platform

Details Cooled turbine vane platform Cooled turbine vane platform

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/04 (2006.01) F01D 25/14 (2006.01)

Patent

CA 2549944

A vane assembly for a gas turbine engine comprises a plurality of airfoils extending between platforms and a plurality of effusion holes which are defined in at least one of the inner and outer platforms in a region intermediate adjacent airfoils. The effusion holes provide fluid flow communication between a cooling air source and the gas path.

Une roue à ailettes pour turbomachine à gaz comprend plusieurs profils s'étendant entre des plateformes et plusieurs orifices d'effusion définis dans au moins une des plateformes intérieure ou extérieure, dans une zone se trouvant entre les profils adjacents. Les orifices d'effusion permettent la communication fluidique entre une source d'air de refroidissement et la voie de passage du gaz.

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