Abstract: A rotor assembly may be used in a gas turbine. The rotor assembly includes rotor segments arranged in succession in an axial direction and interconnected in the axial direction by a tie-rod, and a rotor segment disposed forwardly in the axial direction having a first contact surface and a rotor segment disposed rearwardly in the axial direction having a second contact surface. The first and second contact surfaces are at least partially in contact with each other, are substantially annular in shape, and extend in a radial direction and in a circumferential direction. The first contact surface and/or the second contact surface extend at least partially obliquely relative to the radial direction. An angle is formed between the first contact surface and the second contact surface when viewed in a sectional plane defined by the axial direction and the radial direction.

Abstract: Described is a rotor disk (40) for a compressor (29, 32) of a gas turbine, in particular an aircraft gas turbine (10), the rotor disk having a main body (42), at least one rotor arm (44) projecting from the main body (42) in the axial direction (AR), the rotor arm (44) having, in a sectional view taken in a sectional plane defined by the axial direction (AR) and the radial direction (RR) a beginning portion (44a) merging into the main body (42); an end (44e) portion remote from the main body (42) and forming a kind of free end in the axial direction (AR), the beginning portion (44a) and the end portion (44e) being interconnected by an intermediate portion (44z), characterized in that the intermediate portion (44z) is curved with at least one radius of curvature (Ri, Ra).

Abstract: A rotor assembly may be used in a gas turbine. The rotor assembly includes rotor segments arranged in succession in an axial direction and interconnected in the axial direction by a tie-rod, and a rotor segment disposed forwardly in the axial direction having a first contact surface and a rotor segment disposed rearwardly in the axial direction having a second contact surface. The first and second contact surfaces are at least partially in contact with each other, are substantially annular in shape, and extend in a radial direction and in a circumferential direction. The first contact surface and/or the second contact surface extend at least partially obliquely relative to the radial direction. An angle is formed between the first contact surface and the second contact surface when viewed in a sectional plane defined by the axial direction and the radial direction.

Abstract: A method for repairing a rotor system (2) of a turbomachine, having a rotor (4) which has a groove (26) extending in the circumferential direction (58) of the rotor for accommodating an annular section (18; 28). The method has the following steps: chamfering a notch (40) in the groove (26); introducing a recess (44) into the groove (26); and inserting the annular section (18; 28) into the groove (26). At least one engagement element (48; 49) formed on the annular section (18; 28) engages in the recess (44) in order to form a lock against rotation in the circumferential direction (58).

Abstract: A method for repairing a rotor system (2) of a turbomachine, having a rotor (4) which has a groove (26) extending in the circumferential direction (58) of the rotor for accommodating an annular section (18; 28). The method has the following steps: chamfering a notch (40) in the groove (26); introducing a recess (44) into the groove (26); and inserting the annular section (18; 28) into the groove (26). At least one engagement element (48; 49) formed on the annular section (18; 28) engages in the recess (44) in order to form a lock against rotation in the circumferential direction (58).