| 摘要 |
FIELD: machine building.SUBSTANCE: cooled blade of a gas turbine comprises an airfoil which is set in the flow direction between the leading edge and the rear edge and is limited by respective walls on the suction side and discharge side. The inner space is provided between the walls where the cooling air passes in the flow direction to the rear edge and escapes to outside in the rear edge zone. The wall on the discharge side is ended in the flow direction with the a rim on the discharge side at a distance from the rear edge. The cooling air escapes from the inner space on the discharge side. The inner space at a distance from the rear edge is divided by a variety of ridges oriented in parallel to the flow direction into a variety of cooling channels, which are parallel, providing for pressure differential and fitted by swirlers to enhance cooling effect being additionally installed in them. Immediately before the cooling air escape from the inner space, a portion of flow partitions is provided in the cooling air flow path, the said partitions are distributed across the flow direction and their linear density is less than the linear density of the ridges. A variety of pins in the form of two-dimensional lattice structure is provided between the cooling channels and flow partitions, the pins pass through the inner space across the flow direction between the wall on the suction side and the wall on the discharge side.EFFECT: invention is aimed at the decrease of aerodynamic losses at the rear edge and lower cooling air consumption.4 cl, 2 dwg |
