Method and apparatus for cooling an airfoil

Details Method and apparatus for cooling an airfoil Method and apparatus for cooling an airfoil

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01) F01D 25/12 (2006.01)

Patent

CA 2462986

An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes a plenum longitudinally located within the leading edge of the airfoils. Within the plenum are positioned a plurality of turbulence promoters to provide enhanced heat transfer within the leading edge. Also, the cooling design includes a plurality of inlets to receive cooling air from an internal cavity of the airfoil as well as a plurality of outlets located within a trench on the exterior surface of the leading edge through which the cooling air exits to film cool the leading edge.

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