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 5/14 (2006.01) F01D 5/08 (2006.01) F01D 5/18 (2006.01) F01D 11/04 (2006.01)

Patent

CA 2359291

A turbine blade (30) includes a platform (40) having an internal cavity (108) formed therein 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, and at least one supply passage (110) extends between the internal cooling circuit (54) and the internal platform (40) cavity (108) for diverting coolant to the internal platform (40) cavity (108). The coolant is expelled from holes (112) located in the forward and aft edges of the platform (40) for purging the forward and aft disk wheel spaces (122, 124) and impingement cooling adjacent nozzle bands.

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