CPC F01D 5/3007 (2013.01) [F05D 2220/32 (2013.01); F05D 2250/711 (2013.01); F05D 2250/712 (2013.01)] | 15 Claims |
1. A rotor blade for a gas turbine, the rotor blade comprising:
an airfoil portion; and
a blade root connected to the airfoil portion,
wherein the blade root has a left and a right blade root contour with respect to a cross-sectional view,
wherein, proceeding from a lower end of the blade root, the blade root contour has at least two convex contour portions and at least two concave contour portions,
wherein, proceeding from the lower end along the blade root contour between a convex contour portion and an adjoining concave contour portion, there is provided a contour portion as a flank portion that is load-bearing in operation, and
wherein, proceeding from the lower end along the blade root contour between a concave contour portion and an adjoining convex contour portion, there is provided a contour portion as a flank portion that is not load-bearing in operation,
wherein at least one of the concave contour portions has a first arc portion, a second arc portion, and a straight portion disposed between the two arc portions, and
wherein the first arc portion has a larger first radius than the second arc portion.
|