| 摘要 |
<p>TURBINE BLADE 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.</p> |
