A hollow cooled gas turbine rotor blade or guide vane, wherein the cooling cavities comprise pins interconnected with ribs

摘要

The invention refers to a rotor blade or guide vane airfoil for a gas turbine engine having a longitudinal axis and a source of cooling fluid, the airfoil having a pressure wall, a suction wall, a leading edge, a trailing edge and at least one cooling fluid flow passage. The cooling fluid flow passage is in fluid communication with the source of cooling fluid. Means for directing cooling fluid at least to the trailing edge are provided, whereas the cooling fluid flow passage including: a plurality of axially extending walls, each of the walls extending laterally between the pressure wall and suction wall. The plurality of walls being radially spaced within the cooling fluid flow passage such that adjacent pairs of walls define a channel, the axial spacing between the adjacent walls comprising in radial direction of the airfoil a pins and a ribs structure, wherein the pins holistic or approximately cover the axial height of the channel. The ribs have a deeper level with respect to the pins and the ribs establish a bridge-like connection between each of adjacent ribs.