Axial flow type fan, compressor and turbine blade modification method, and blade obtained by the modification

摘要

Provided is a blade on which a secondary flow loss is reduced without changing aerodynamic design of a base blade. The blade includes: a base blade part and an elevated portion which is provided on a pressure side in the vicinity of a trailing edge in at least one of a hub region and a tip region of the base blade part, an aerofoil profile in a position in a spanwise direction where the elevated portion is provided is obtained by modifying, to a modified trailing edge portion curve, a trailing edge portion curve of a base aerofoil profile, the modified trailing edge portion curve is constituted of a portion of the trailing edge portion curve of the base aerofoil profile in the position in the spanwise direction where the elevated portion is provided and an elevated portion curve, the portion being further on a side of a suction side curve than the trailing edge, the elevated portion curve is constituted of a concave front side curve and a convex rear side curve, the rear side curve is a part of an ellipse or a circle, and the front side curve is a curve smoothly connecting the rear side curve and a pressure side curve.