| 摘要 |
A turbine blade (10) including an airfoil (12) defining an airfoil cavity- forming a cooling system in the blade. First, second and third ribs (64a, 64b, 64c) are positioned in the airfoil cavity to form first, second and third generally elongated cooling cavities (66a, 66b, 66c) along at least a portion of the span-wise direction of the airfoil in an area adjacent the trailing edge (24) of the airfoil. Each of the ribs includes a plurality of orifices (68) for conveying a cooling fluid into each of the cavities. Each of the cavities includes a pair of converging pressure and suction sidewalls (74, 76), angling inwardly relative to an outer surface (82, 84)of the airfoil such that the thickness of the airfoil pressure and suction sidewalls (18, 20) increases along said first, second and third coding contries (66a, 66b, 66c) in the direction of coding fluid flow to increase the impingement of cooling fluid from the orifices onto the cavity walls, and increase the cooling effectiveness within the trailing edge of the airfoil. |
