Cooled gas turbine blade

Details Cooled gas turbine blade Cooled gas turbine blade

F - Mech Eng,Light,Heat,Weapons

01

D

170/71

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

Patent

CA 1087527

COOLED GAS TURBINE BLADE ABSTRACT OF THE DISCLOSURE A cooled gas turbine blade having two separate serpentine coolant flow paths, each having an entry in the blade root and an exhaust in the blade tip. The initial leg of one path is in flow communication with a chamber adjacent the leading edge of the blade through a plurality-of small openings along the radial extent of the airfoil portion for impingement cooling the leading edge with relatively high pressure, low temperature coolant. The chamber is exhausted through a blade tip opening and a platform opening which are related in size to maximize impingement cooling affect at a predetermined radial portion of the leading edge. The flow paths are configured to minimize pressure drop therein and enhance the effectiveness of the coolant.

294987

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