Abstract: A centrifugal gas compressor or pump comprising a body, a wheel rotatably mounted within the body around a wheel axis, the wheel comprising a hub, a set of blades fastened to the hub, the body comprising a diffuser placed on the periphery of the wheel and a fluid intake placed facing the hub, the blades comprising a first edge facing the intake and a second edge facing the diffuser so that a fluid travels from the intake to the diffuser, the second edges being located inside a blade-enveloping cylinder centred on the wheel axis. The wheel comprises a toothed ring fastened to the wheel, which extends radially past the enveloping cylinder to form a diffuser wall.

Abstract: The invention relates to a fan platform of a bypass turbomachine having a primary stream and a secondary stream. The platform defines a portion of the surface of the nose around which the primary stream flows and that carries blades extending radially outwards from said platform. Between two adjacent blades, the platform has at least one rib projecting into the space between the two blades, said rib being designed to participate in compressing the primary air stream.

Abstract: The invention relates to a turbojet compressor comprising a shroud and a plurality of blades, each fixed via its root to the shroud. Level with each blade root, the shroud presents a suction-side ramp and a pressure-side ramp extending from the trailing edge of the blade to beyond its leading edge. The pressure-side and suction-side ramps join together upstream from the leading edge of the blade to form a projection presenting a profile that is twisted about the axis of the shroud so as to force the gas stream flowing in each flow passage to go round the blade root essentially on the suction-side thereof, and the suction-side ramp presents a profile that is inclined relative to the outside surface of the shroud so as to deflect the gas stream flowing in the corresponding flow passage from the suction-side surface of the blade towards the pressure-side surface of the adjacent blade.

Abstract: The invention relates to a turbojet compressor comprising a shroud and a plurality of blades, each fixed via its root to the shroud. Level with each blade root, the shroud presents a suction-side ramp and a pressure-side ramp extending from the trailing edge of the blade to beyond its leading edge. The pressure-side and suction-side ramps join together upstream from the leading edge of the blade to form a projection presenting a profile that is twisted about the axis of the shroud so as to force the gas stream flowing in each flow passage to go round the blade root essentially on the suction-side thereof, and the suction-side ramp presents a profile that is inclined relative to the outside surface of the shroud so as to deflect the gas stream flowing in the corresponding flow passage from the suction-side surface of the blade towards the pressure-side surface of the adjacent blade.

Abstract: The invention relates to a fan platform of a bypass turbomachine having a primary stream and a secondary stream. The platform defines a portion of the surface of the nose around which the primary stream flows and that carries blades extending radially outwards from said platform. Between two adjacent blades, the platform has at least one rib projecting into the space between the two blades, said rib being designed to participate in compressing the primary air stream.

Abstract: Several embodiments of devices for intaking gases from the boundary layer through ducts (3, 4) hollowed out in blades (7) are disclosed. These embodiments are characteristic in that they are suitable for variable setting blades, installed on the stator (1) using pivots (8). The seal is maintained despite the variation in the relative position between the moving pivots (8) through which ducts pass, and the fixed intake header pipe (10).