| 摘要 |
A cavity 22, in a turbine blade, is subdivided by radially extending webs 32, 34, to define passages 24, 26, 28 for a flow K, of cooling fluid. The web 34, adjacent the trailing edge of the blade, is provided with one or more through passages 36, close to the blade tip, thereby promoting cooling in the tip region and avoiding flow separation of the coolant as it changes direction between passages 24, 26. The through passages 36, may have a varying cross-sectional profile (fig. 2) and flow guiding webs (40)(figs. 2-4) may be provided down-stream of the passages. The webs (40) may be curved (fig. 2), segmented (fig. 3) or continuous ( fig. 4). Ribs 52, pins 56, semi-cylinders, or spherical sections may be provided to enhance heat transfer.
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