| 摘要 |
PROBLEM TO BE SOLVED: To provide a novel method of cooling tip shrouds of a turbine bucket. SOLUTION: Localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shrouds 120, 220, 420. One or more airfoil cooling passages are provided in an airfoil portion of the turbine bucket, and one or more cooling chambers 130, 142, 230, 242, 342, 430 are provided in the shroud. Cooling air from one or more airfoil cooling passages hits the wall faces of one or more cooling chambers through one or more impingement holes 132, 232, 432, and the used impingement cooling air is exhausted from one or more outlet openings 136, 138, 140, 236, 240 of the cooling chambers. COPYRIGHT: (C)2008,JPO&INPIT |
