Internally cooled airfoil for a gas turbine engine and method

Details Internally cooled airfoil for a gas turbine engine and method Internally cooled airfoil for a gas turbine engine and method

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01) F01D 9/02 (2006.01)

Patent

CA 2528724

An internally-cooled airfoil for a gas turbine engine, wherein the airfoil comprises at least one substantially chordwise-extending and internally-projecting stiffener located on an internal surface of one of the sidewalls and adjacent to the insert.

Surface portante à refroidissement interne pour moteur à turbine à gaz qui comprend au moins un raidisseur essentiellement dans la direction longitudinale de la surface portante et s'étendant vers l'intérieur qui se trouve sur une surface interne de l'une des parois latérales, de manière adjacente par rapport à la pièce insérable.

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