Patent ID: 7367775

Claim:
A rotor for a gas turbine, having blades forming a blade ring and the blades within the blade ring being arranged at a different distance from one another and thus with a different blade pitch, a distance between the blades within the blade ring changing continuously or discontinuously in a circumferential direction and the distance between the blades within the blade ring dimensioned such that an imbalance is canceled out, wherein the rotor has a first rotatable blade ring and a second rotatable blade ring arranged axially behind one another in the rotor, wherein, within each of the first and second blade rings of the rotor the blades are arranged at a different distance from one another, and wherein a first arrangement of the different distances of the blades within the first blade ring of the rotor is different from a second arrangement of the different distances of the blades within the second blade ring of the rotor.