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A turbomachine compressor, including an air bleed device including a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor is disclosed. A screen sheet of annular shape is mounted radially inside the casing facing a

A turbomachine compressor, including an air bleed device including a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor is disclosed. A screen sheet of annular shape is mounted radially inside the casing facing a portion of the suction end of the duct so as to make the bleeding of air uniform over 360° around the axis of the compressor.

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1. A compressor, including air bleed means comprising a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage arranged coaxially with the compressor, wherein a screen sheet of annular shape is mounted radially inside the outer casing

1. A compressor, including air bleed means comprising a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage arranged coaxially with the compressor, wherein a screen sheet of annular shape is mounted radially inside the outer casing facing a portion of the suction end of the duct, andwherein the screen sheet extends over less than 360° and includes circumferential ends each having a rim of cylindrical shape, the rims bearing radially against a flange of the outer casing and defining an annular space between them and between the screen sheet and the flange. 2. A compressor according to claim 1, wherein the sheet has a downstream end fastened by screws to an annular flange of the stator stage mounted downstream from the rotor wheel. 3. A compressor according to claim 2, wherein the screen sheet extends over about 234° and the cylindrical rims at the circumferential ends of the screen sheet extend angularly over several tens of degrees. 4. A compressor according to claim 2, wherein the downstream end of the screen sheet includes holes of larger diameter disposed alternately with holes of smaller diameter for passing fastener screws. 5. A compressor according to claim 2, wherein the screen sheet is mounted with resilient prestress to bear against the flange of the casing. 6. A compressor according to claim 2, wherein a stator stage situated upstream from the rotor wheel is fastened to the flange of the casing by a shroud that includes holes, with those that are angularly situated level with the suction end of the duct and a central portion of the screen sheet being totally covered. 7. A compressor according to claim 6, wherein the holes in the shroud facing axially the circumferential end portions of the screen sheet are 50% covered. 8. A compressor according to claim 1, wherein the screen sheet includes at least one orifice for passing an endoscope. 9. A screen sheet of annular shape for use in a compressor according to claim 1, wherein the screen sheet section is L-shaped. 10. A screen sheet according to claim 9, comprising a cylindrical wall connected at a first end to a radial wall having holes for passing fastener screws and connected at a second end to a frustoconical wall. 11. A screen sheet according to claim 10, wherein the circumferential ends of the frustoconical wall includes radial rims facing outwards. 12. A turbomachine including a compressor according to claim 1. 13. A turbomachine according to claim 12, wherein the turbomachine is an airplane turboprop or a turbojet. 14. A compressor according to claim 1, wherein the cylindrical rims are provided on an upstream end of the screen sheet.