| 摘要 |
A turbine airfoil 12 includes a plurality of internal ribs 34,36 joined to laterally opposite first and second sidewalls (16,18, fig 2) to define serpentine cooling circuits 38a,38b therein. A span rib 34 extend longitudinally between a root 26 and tip 28 of the airfoil, and slant ribs 36a,36b extend outwardly from opposite sides of the span rib 34 to define respective portions of the serpentine circuits 38a,38b, and slant ribs 36c,36d extend inwardly from the leading and trailing edges 20,22.
|
