Rotor for a gas turbine

摘要

A rotor for a gas turbine exhibits three-dimensionally curved blades which are curved counter to the direction of rotation of the rotor in the radial flow region. The blades are arranged on a hub with a disc-shaped terminal region. In order to achieve a more highly aerodynamic blade shape with a simultaneous reduction of the moment of inertia of the rotor, the blades exhibit in the axial direction mean camber lines which extend centrally in the radial direction between the pressure side and the suction side of the blades, the mean camber lines being describable by a 2nd order curve equation.