| 摘要 |
For cooling in turbine gas temperatures in excess of 1260 degrees C a gas turbine blade has an internal coolant passage 28 of width D and a plurality of longitudinally spaced substantially straight turbulator ribs 52 having a height E disposed substantially perpendicularly to the longitudinal axis of the coolant passage. The ratio E/D is within the range of about 0.07 and about 0.33 and the height E of the ribs lies 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 without the need for conventional, relatively complex cooling structures required for larger blades. <IMAGE> |
