| 摘要 |
A gas turbine nozzle includes a row of stator vanes 32 extending radially between inner and outer bands 34, 36. The vanes 32 include opposite pressure and suction sidewalls and opposite leading and trailing edges 42, 44. Each vane 32 includes an inner pattern of cooling holes 52 and an outer pattern of cooling holes 54 distributed along the leading edge 42. The inner and outer cooling holes 52, 54 are inclined such that they diverge toward the inner and outer bands 34, 36 respectively. The inner and outer cooling holes 52, 54 may comprise multiple radial columns laterally spaced along the pressure and suction sidewalls parallel to the leading edge 42. A plurality of transition holes 56 may be provided along the leading edge 42 near the mid-span thereof to radially adjoin the inner and outer patterns of holes 52, 54.
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