F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
170/81
F01D 5/12 (2006.01) F01D 5/18 (2006.01)
Patent
CA 1211052
TURBINE BLADE ABSTRACT OF THE DISCLOSURE An exemplary preferred embodiment of the present invention includes a gas turbine blade having an internal coolant passage therein of width D and a plurality of longitudinally spaced substantially straight turbulator ribs having a height E disposed substantially perpendicularly to a longitudinal axis of the coolant passage The ratio E/D is preferably within the range of about 0.07 and about 0.33 and the height E of the ribs being in the range of about 0.010 inches and about 0.025 inches These features may be utilized in a relatively small blade, e.g., 1.0 inch, for obtaining enhanced cooling ability for operation in turbine gas temperatures greater than about 2,300 degrees F without the need for conventional, relatively complex cooling structures required for larger blades.
481264
Company General Electric
Eckersley Raymond A.
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