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A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades be

A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z2).

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1. A bladed rotor for a turbomachine, comprising a plurality of blades distributed around a circumference of the bladed rotor; wherein a blade distribution of the plurality of blades is a natural-number sector count (Z) of first angular sectors and second angular sectors; a first blade count of firs

1. A bladed rotor for a turbomachine, comprising a plurality of blades distributed around a circumference of the bladed rotor; wherein a blade distribution of the plurality of blades is a natural-number sector count (Z) of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count,each of the first and second angular sectors extending around an angle equal to 360 degrees divided by 2Z and where each first angular sector adjoining on both sides with the second angular sectors, and each second angular sector adjoining on both sides with the first angular sectors;wherein the natural number sector count is odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2). 2. The rotor as recited in claim 1, wherein the first blades in the first angular sectors and the second blades in the second angular sectors are at least substantially identical. 3. The rotor as recited in claim 1, wherein the first blades in the first angular sectors and/or the second blades in the second angular sectors are distributed at least substantially equidistantly from each other. 4. The rotor as recited in claim 2, wherein the first blades in the first angular sectors and/or the second blades in the second angular sectors are distributed at least substantially equidistantly from each other. 5. The rotor as recited in claim 1, wherein a distance between a first blade adjacent to a second angular sector and a second blade adjacent to this first blade is at least substantially equal to half the sum of the distance between this first blade and a first blade adjacent thereto and the distance between this second blade and a second blade adjacent thereto. 6. The rotor as recited in claim 2, wherein a distance between a first blade adjacent to a second angular sector and a second blade adjacent to this first blade is at least substantially equal to half the sum of the distance between this first blade and a first blade adjacent thereto and the distance between this second blade and a second blade adjacent thereto. 7. The rotor as recited in claim 1, wherein the first and second blade counts differ by an odd integral number. 8. The rotor as recited in claim 7, wherein the odd integral number is one. 9. The rotor as recited in claim 1, wherein the sector count is three (Z=3), and the angular sectors each have 60°. 10. The rotor as recited in claim 2, wherein the sector count is three (Z=3), and the angular sectors each have 60°. 11. The rotor as recited in claim 4, wherein the sector count is three (Z=3), and the angular sectors each have 60°. 12. The rotor as recited in claim 5, wherein the sector count is three (Z=3), and the angular sectors each have 60°. 13. The rotor as recited in claim 1, wherein the sector count is four (Z=4), and the angular sectors each have 45°. 14. The rotor as recited in claim 2, wherein the sector count is four (Z=4), and the angular sectors each have 45°. 15. The rotor as recited in claim 4, wherein the sector count is four (Z=4), and the angular sectors each have 45°. 16. The rotor as recited in claim 5, wherein the sector count is four (Z=4), and the angular sectors each have 45°. 17. The rotor as recited in claim 1, wherein the blades are formed integrally with a hub. 18. A aircraft engine gas turbine, comprising at least one rotor according to claim 1.