Turbine blade for gas turbine engine and method of cooling same

Details Turbine blade for gas turbine engine and method of cooling same Turbine blade for gas turbine engine and method of cooling same

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01)

Patent

CA 2359288

A turbine blade (30) includes a platform (40) and an airfoil (42) extending radially from the platform (40). An internal cooling circuit (54) is formed in the airfoil (42) for circulating a coolant therethrough to cool the airfoil (42). At least one supply passage (110) is provided to direct some of the coolant that has passed at least partially through the internal cooling circuit (54) onto the platform (40) for cooling the platform (40).

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