Blade of a turbomachine with block-wise defined profile skeleton line

摘要

A turbomachine blade with a profile skeleton line extending along a meridional flow line, the blade being radially divided into at least three zones (Z 0, Z 1, Z 2 ) with profile skeleton lines of each zone (Z 0, Z 1, Z 2 ) provided in each zone from the respective radially inner to the radially outer boundary to satisfy the equations: ${\mathrm{alpha}}^{*}=\frac{{\mathrm{alpha}}_1-{\mathrm{alpha}}_P}{{\mathrm{alpha}}_1-{\mathrm{alpha}}_2}$ $S^{*}=\frac{s_P}{S}$ where P is any point of the profile skeleton line, alpha₁ is angle of inclination at blade leading edge, alpha₂ is angle of inclination at blade trailing edge, alpha* is dimensionless, specific angle of total curvature, S* is dimensionless; specific extension, alpha_P is angle of tangent at any point P of profile skeleton line to central meridional flow line, s_P is extension of profile skeleton line at any point P, and S is total extension of profile skeleton line.