Patent ID: 8038409

Claim:
A turbomachine having at least one high load blade row of rotor blades designed for work coefficients defined by a specific enthalpy transformation Δh relative to a square of a rotor blade velocity U, which, in at least one of its center section and averaged over a blade height, provides for an essentially swirl-free relative outflow, wherein the respective rotor blades in their trailing edge area are essentially orientated in a meridional direction m, with at least one of entry metal angles of the rotor blades at the center section ε 1m and entry metal angles of the rotor blades averaged over the height of the rotor blades ε 1G being >40 degrees and at least one of exit metal angles of the rotor blades at the center section ε 2M and exit metal angles of the rotor blades averaged over the height of the rotor blades ε 2G ranging from −10 to +5 degrees; wherein, a center line between a pressure side (DS) and a suction side (SS) of a blade profile, determined in a plane of a section of the blade profile, forms a profile skeleton line, with tangents T VK and T HK drawn to the profile skeleton line at leading and trailing edge points (VK, HK) to quantify an orientation of the profile, the entry metal angles being established between tangent T VK and the meridional direction m, the exit metal angles between the tangent T HK and the meridional direction m.