Cooling device for gas turbine components

摘要

Mounting platforms (20) which support gas turbine blades are subjected to hot gas flows which can enter the gaps (12) between segments. The heating effect is reduced by shaping the segment edges (30) on the downstream side of each gap. This produces a velocity component in the hot gas flow, normal to the gap and draws in cooling gas flows through the gap or through cooling ducts in the segments. The cooling gasses form a barrier layer over the segments without affecting gas turbine performance.