| 摘要 |
A turbomachinery component (100) includes an airfoil section with a cooling passage (142) extending within the airfoil section. A wall (150) is defined between the cooling passage and an exterior surface (146) of the airfoil. At least one row (132; 134; 136; 138; 139) of cooling holes (130) is positioned along a cooling portion (160) of the external wall proximate a leading edge (112) of the airfoil for fluid communication between the cooling passage and the exterior surface of the airfoil. The cooling portion of the airfoil wall is thicker than an average adjacent airfoil wall thickness. |
