| 摘要 |
On a platform cooling arrangement for the nozzle guide vane stator of a gas turbine arranged downstream of the combustion chamber, one or several parallel row(s) of cooling-air ejection ducts ( 10 ) are arranged continuously or in groups on the circumference. The cooling-air ejection ducts are angled relative to the axial direction at an angle (alpha) to produce a vortex structure on the surface of the platform ( 2 ) which, on the one hand, reduces mixing of the cooling air jets ( 11 ) with the hot gas flow ( 8 ) and, on the other hand, ensures complete cooling of the area of boundary layer separation ( 12 ) downstream of a boundary layer separation line ( 13 ) up to the suction side ( 14 ) of the adjacent nozzle guide vane ( 1 ).
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