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 is decreasing monotonically over the length of each of said sections , 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 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 , 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 is decreasing monotonically over the length of each of said sections , 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 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 , 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 . <EOS>