Turbomachine rotor blade

1. A turbomachine rotor blade comprising:

a blade root and a blade tip spaced apart by a blade height;

at least one intermediate segment between the blade root and the blade tip that presents forward sweep over at least 50% of the blade height; and

a distal segment with backward sweep between the at least one intermediate segment and the blade tip, the distal segment also presenting, from the at least one intermediate segment to the blade tip, a positive tangential angle of inclination in a direction of rotation of a rotor.

2. A turbomachine rotor blade according to claim 1 , wherein the distal segment presents a positive tangential angle of inclination, in the direction of rotation of the rotor, that is more pronounced than that of the at least one intermediate segment.

3. A turbomachine rotor blade according to claim 1 , wherein the at least one intermediate segment also presents a positive tangential angle of inclination, in the direction of rotation of the rotor, over at least one zone adjacent to the distal segment.

4. A turbomachine rotor blade according to claim 1 , wherein the distal segment occupies at least 5% of the blade height.

5. A turbomachine rotor blade according to claim 4 , wherein the distal segment occupies at least 8% of the blade height.

6. A turbomachine rotor blade according to claim 1 , wherein the distal segment occupies no, more than 30% of the blade height.

7. A turbomachine rotor blade according to claim 6 , wherein the distal segment occupies no more than 15% of the blade height.

8. A single-piece bladed disk comprising a plurality of blades according to claim 1 .

9. A compressor rotor comprising a plurality of blades according to claim 1 .

10. A fan rotor comprising a plurality of blades according to claim 1 .