COMPRESSOR BLADE FOR GAS TURBINE, AND GAS TURBINE

摘要

PROBLEM TO BE SOLVED: To prevent the progress of a crack with damage as an origin even with the generation of damage to the tip of an airfoil in a compressor blade for a gas turbine. SOLUTION: A compressor blade 1 of a gas turbine comprises an airfoil 2 and a dovetail 3. The airfoil 2 is formed in plate shape and has a pressure-side side face 4 and a suction-side side face 5. An airfoil front edge 6 is formed on the front side of the airfoil 2, and an airfoil rear edge 7 is formed on the rear side. The tip of the airfoil 2 is formed in flat shape. This flat part 8 intersects a compression-side side face 4 to form an angular part 9, and the flat part 8 intersects the suction-side side face 5 to form an angular part 10. The flat part 8 at the tip of the airfoil 2 is provided with a compression residual stress part (oblique line part).