Coolant passage structure especially for cast rotor blades...

Details Coolant passage structure especially for cast rotor blades... Coolant passage structure especially for cast rotor blades...

F - Mech Eng,Light,Heat,Weapons

01

D

170/68

F01D 5/18 (2006.01)

Patent

CA 1262868

9 50,078 ABSTRACT OF THE DISCLOSURE A combustion turbine rotor blade is provided with an airfoil portion having a plurality of coolant holes extending radially outwardly therethrough. The coolant holes are tapered to a smaller flow cross-section in the radially outward direction to produce more uniform cooling action over the length of the holes over which tapering is provided.

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