Internally cooled gas turbine airfoil and method

Details Internally cooled gas turbine airfoil and method Internally cooled gas turbine airfoil and method

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01)

Patent

CA 2513045

An internally cooled airfoil for a gas turbine engine and a method of cooling in which at least two substantially parallel passages are in fluid communication with an exit plenum and adapted to reduce stagnation and improve strengthening, particularly in wide chord blades.

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