| 摘要 |
<p>An aerofoil cooling system 38, especially for a gas turbine engine nozzle guide vane, comprising a baffle 158 and a cooling fluid flow path 154 is disclosed. The baffle is disposed within the cooling fluid flow path, and the cooling fluid flow path comprises an internal passage 146 of an aerofoil. The baffle has a single through bore 162 inset and discrete from an outer perimeter 160 of the baffle that provides the only fluid communication path through the baffle to the cooling fluid flow path on opposite sides of the baffle. Preferably the system includes two cooling fluid sources with the cooling fluid flow path in between. The through bore may be a circular hole in the centre of the baffle. The baffle may be located at one end of the internal passage and include a skirt around the perimeter.</p> |
