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A rotor of a turbo engine, e.g., a gas turbine rotor, has a rotor base member, the rotor base member having a groove extending in the circumferential direction of the rotor base member, and having a plurality of rotor blades, each rotor blade having a blade, a blade root and a blade platform positio

A rotor of a turbo engine, e.g., a gas turbine rotor, has a rotor base member, the rotor base member having a groove extending in the circumferential direction of the rotor base member, and having a plurality of rotor blades, each rotor blade having a blade, a blade root and a blade platform positioned between the blade and the blade root, and the rotor blades being anchored in the groove of the rotor base member by their blade roots. The groove and the blade roots have a profile, such that the blade roots of the rotor blades are insertable by a tilting motion or swiveling motion into the circumferentially extending groove of the rotor base member, and in the circumferential direction, a width of the blade root corresponds approximately to a width of the blade platform of the specific rotor blade.

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What is claimed is: 1. 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

What is claimed is: 1. 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. 2. The rotor according to claim 1, wherein the rotor is arranged as a gas turbine rotor. 3. The rotor according to claim 1, wherein the spacers are positioned between groove-wall side pieces of the groove and the blade platforms of the rotor blades. 4. The rotor according to claim 1, wherein the securing devices include rivets. 5. The rotor according to claim 1, wherein the projections are integral to the groove-wall side pieces and extend radially outwardly starting from the groove-wall side pieces. 6. The rotor according to claim 1, wherein the the projections are closed in the circumferential direction of the groove, extend in the radial direction and are integral to the groove-wall side pieces. 7. A rotor of a turbo engine, comprising: a rotor base member including a groove extending in a circumferential direction of the rotor base member; and 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; 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 spacer on one groove-wall side piece of the groove includes a projection that is closed in the circumferential direction of the groove, extends in the radial direction and is integral to the groove-wall side piece; and wherein the spacer on another groove-wall side piece of the groove includes one of (a) a closure ring that is closed in the circumferential direction and (b) a closure ring that is segmented in the circumferential direction, is insertable between the another groove-wall side piece and the platforms of the rotor blade and is immobilized by a retaining ring. 8. The rotor according to claim 6, wherein the projections extend in the circumferential direction of the groove and are interrupted by at least one opening. 9. A gas turbine, comprising: at least one rotor including: 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. 10. The gas turbine according to claim 9, wherein the gas turbine is arranged as a gas turbine of an aircraft engine.