An airfoil rotor turbine blade, comprising: • a leading edge, • a root section, wherein the root section comprises a first curved controlled flow section, • a tip section, wherein the tip section comprises a second curved controlled flow section, and • a plurality of mean sections positioned between the root section and the tip section, and wherein the plurality of mean sections each comprising a prismatic shape, wherein said first curved controlled flow section, said second curved controlled flow section and said plurality of mean sections are distributed along the leading edge, wherein blade outlet angle of the first and the second curved controlled flow section (310, 320) is decreasing monotonically over the length of each of said sections (310, 320), wherein blade outlet angle of a blade is the angle, relative to the circumferential direction of a rotor, that the working fluid leaves a circumferential blade row, wherein the first and second curved controlled flow sections (310, 320) curve outward away from the mean sections such that the mean sections have a reduced axial width in comparison to the first and second curved controlled flow sections (310, 320), and wherein said axial width is the distance between the leading and trailing edges as measured along the rotational axis A of a turbine, wherein the first controlled flow section defines a first decreasing blade outlet angle, the second controlled flow section defines a second decreasing outlet angle, and the plurality of mean sections define a constant blade outlet angle, and wherein the plurality of mean sections has a ratio of a throat dimension to a pitch dimension constant with the tolerance of up to ±0.1, and wherein a ratio of a throat dimension to a pitch dimension for the first controlled flow section and a ratio of a throat dimension to a pitch dimension for the second controlled flow section are lower than the ratio of a throat dimension to a pitch dimension for the plurality of mean sections. • a leading edge, • a root section, wherein the root section comprises a first curved controlled flow section, • a tip section, wherein the tip section comprises a second curved controlled flow section, and • a plurality of mean sections positioned between the root section and the tip section, and wherein the plurality of mean sections each comprising a prismatic shape, wherein said first curved controlled flow section, said second curved controlled flow section and said plurality of mean sections are distributed along the leading edge, wherein blade outlet angle of the first and the second curved controlled flow section (310, 320) is decreasing monotonically over the length of each of said sections (310, 320), wherein blade outlet angle of a blade is the angle, relative to the circumferential direction of a rotor, that the working fluid leaves a circumferential blade row, wherein the first and second curved controlled flow sections (310, 320) curve outward away from the mean sections such that the mean sections have a reduced axial width in comparison to the first and second curved controlled flow sections (310, 320), and wherein said axial width is the distance between the leading and trailing edges as measured along the rotational axis A of a turbine, wherein the first controlled flow section defines a first decreasing blade outlet angle, the second controlled flow section defines a second decreasing outlet angle, and the plurality of mean sections define a constant blade outlet angle, and wherein the plurality of mean sections has a ratio of a throat dimension to a pitch dimension constant with the tolerance of up to ±0.1, and wherein a ratio of a throat dimension to a pitch dimension for the first controlled flow section and a ratio of a throat dimension to a pitch dimension for the second controlled flow section are lower than the ratio of a throat dimension to a pitch dimension for the plurality of mean sections.