Turbine vane, for a gas turbine, has inner cooling channels in a serpentine structure, with flow connections through hairpin bends

摘要

The turbine vane (1), for a gas turbine, has inner cooling channels (15a-15c) in a serpentine configuration extending radially outwards and inwards. The channels have a flow link between them through hairpin bends (16,20) of 180[deg]. The hairpin bends are at the foot zone of the turbine vane, to connect a radially inwards channel with a radially outwards channel, through the side walls (15d,15e) of the coolant channel which is aligned radially inwards to the inner end of the vane foot (2). The bend is defined by an end plate (21) at the radially inner ends of the coolant channel side walls. Protective strips are placed at the casting where the channel openings are to be drilled by laser beams.