Turbine rotor blade for subsonic flow.

摘要

On a turbine rotor blade for subsonic flow with a profile contour, convexly curved in the area of the leading edge and over the greater part of the suction side (S) and with a profile contour concavely curved in the area of the pressure side (D), the profile contour in the suction side trailing edge area is of concave (K) design. In this area the momentum deficit thickness determining the profile loss is thereby reduced.