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A turbomachine compressor rotor including at least two blade-carrying disks mounted on a common axis and connected together by a wall forming a substantially cylindrical surface of revolution, and a centripetal air bleed mechanism including air passages passing through the wall and radial fins for d

A turbomachine compressor rotor including at least two blade-carrying disks mounted on a common axis and connected together by a wall forming a substantially cylindrical surface of revolution, and a centripetal air bleed mechanism including air passages passing through the wall and radial fins for deflecting a stream of air leaving the passages in the wall, the fins being carried by one of the disks and being substantially in radial alignment with the passages through the wall.

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1. A turbomachine compressor rotor, comprising: first and second blade-carrying disks on a common axis and connected together by a coaxial wall forming a substantially cylindrical surface of revolution, the first blade-carrying disk being located upstream of the second blade-carrying disk on said co

1. A turbomachine compressor rotor, comprising: first and second blade-carrying disks on a common axis and connected together by a coaxial wall forming a substantially cylindrical surface of revolution, the first blade-carrying disk being located upstream of the second blade-carrying disk on said common axis; andcentripetal air bleed means comprising air passages passing through the wall and opening out into an annular chamber formed inside the wall and between the disks, and substantially radial fins carried by an annular element fixed to one of the disks and having two axial ends,wherein the fins are axially spaced apart from the disks and are substantially in radial alignment with the passages through the wall, each of the fins being connected solely by one of the axial ends to a support fastened to the disk, and each of the fins has another of said axial ends being a free end which extends upstream of said one of the axial ends whereby said free end can be in contact with a first portion of said bleed air leaving the air passages while a second portion of said bleed air can flow between said annular element and the second blade-carrying disk. 2. A rotor according to claim 1, wherein the fins are regularly distributed around the axis of the rotor. 3. A rotor according to claim 1, wherein each fin is inclined relative to a radius passing through the axis of the rotor. 4. A rotor according to claim 1, wherein the fins are plane plates. 5. A rotor according to claim 1, wherein the fins are airfoils, each having a radially outer leading edge and a radially inner trailing edge. 6. A rotor according to claim 1, wherein the fins are connected to the disk independently of one another. 7. A rotor according to claim 6, wherein said annular element presents a substantially radial orientation. 8. A rotor according to claim 1, wherein the fins are fitted and fastened to said annular element that is substantially radial, and said annular element is fastened to an annular flange of the second blade-carrying disk by a nut-and-bolt type fastener. 9. A rotor according to claim 1, wherein the radially outer ends of the fins are radially spaced apart from the wall including the air passages by a given distance. 10. A rotor according to claim 1, wherein the fins extend over a fraction of the radial dimension of the disk supporting the fins. 11. A rotor according to claim 1, wherein the air passages are formed through the wall downstream from a labyrinth seal for co-operating with a nozzle mounted between the two disks of the rotor, and the fins are carried by the downstream disk defining the chamber. 12. A rotor according to claim 1, wherein the fins have an axial dimension less than half the axial distance between the disks. 13. A turbomachine, an airplane turboprop, or turbojet, comprising a rotor according to claim 1. 14. A rotor according to claim 1, wherein said free end of each of said fins extends parallel to a radial axis of the fin. 15. A turbomachine compressor rotor, comprising: at least two blade-carrying disks on a common axis and connected together by a wall forming a substantially cylindrical surface of revolution; andcentripetal air bleed means formed apart from the disks, at an axial distance therefrom, and comprising air passages passing through the wall and opening out into an annular chamber formed inside the wall and between the disks, and substantially radial fins carried by an annular element fixed to one of the disks and having a first axial end and a second axial end,wherein the fins are axially spaced apart from the disks and each fin in a substantially radial alignment with the corresponding passage through the wall, each of the fins being connected solely by the first axial end to support means that are fastened to the disk, so that each of the fins has the second axial end being free whereby said second axial end can be in contact with a first portion of said bleed air leaving the air passages while a second portion of said bleed air: can flow between the annular element of said fin and the blade-carrying disk the support means of which is fastened to, andcan pass through said support means. 16. A rotor according to claim 15, wherein: the rotor further comprises a nozzle formed by an annular row of stationary nozzle vanes,the coaxial wall and the nozzle carry elements adapted to form a seal therebetween, and,the air passages pass through the coaxial wall downstream the seal.