Patent ID: 7708529

Claim:
A rotor of a turbo engine, comprising: a rotor base member including a groove extending in a circumferential direction of the rotor base member; a plurality of rotor blades, each rotor blade including a blade, a blade root and a blade platform positioned between the blade and the blade root, the rotor blade anchored in the groove by the blade root; and securing devices that define a relative position in the circumferential direction between the rotor blades and the rotor base member; wherein the groove and the blade root are profiled so that the blade root is insertable into the groove by one of (a) a tilt motion and (b) a swivel motion, in the circumferential direction, a width of the blade root corresponding approximately to a width of the blade platform; wherein a relative position between the rotor blades and the rotor base member in a radial direction is defined by spacers; wherein the spacers include projections positioned on at least one side of the groove; wherein the projections include a plurality of projections positioned at a distance from one another in the circumferential direction on both groove-wall side pieces of the groove, a recess formed between adjacent projections on the respective groove-wall side piece, two rotor blades supported with the blade platforms on each of two opposing projections positioned on different groove-wall side pieces of the groove; wherein the securing devices extend through the two opposing projections positioned on different groove-wall side pieces of the groove.