Abstract: The invention relates to a centrifugal deaerator for an air/oil mixture of a turbomachine, comprising: an annular housing (10) for the centrifugal separation of said mixture, arranged around a hollow shaft (11); axial inlets (14) for the flow of said air/oil mixture into said housing (10); a pinion (20) for rotating said housing (10); and radial oil outlets (15) and oil-free air outlets (16), characterised in that it comprises a metal foam (50) housed in said housing (10) by partially extending along the axial direction (XX?) so as to define two successive spaces, a foam-free space (51) and a foam-lined space (52), said foam-free space opening up towards said axial inlets. A device can be advantageously added to the hollow shaft in order to reduce the free-vortex phenomenon and to thereby significantly reduce the load losses of the deaerator.

Abstract: A centrifugal deaerator for an air/oil mixture of a turbine engine includes: an annular housing arranged around a hollow shaft and having an outer annular wall and an inner annular wall; axial mixture inlets for the inflow of the air/oil mixture into annular housing; a pinion for rotating the annular housing, the pinion including a web that is securely connected to the hollow shaft and to the inner and outer annular walls; radial oil outlets in the outer wall; and oil-free air outlets in the inner wall. The axial mixture inlets and the radial oil outlets are axially arranged on either said of the web to prevent the axial mixture inlets from reintroducing oil evacuated by radial oil outlets into the annular housing.

Abstract: A centrifugal deaerator for an air/oil mixture of a turbine engine includes: an annular housing arranged around a hollow shaft and having an outer annular wall and an inner annular wall; axial mixture inlets for the inflow of the air/oil mixture into annular housing; a pinion for rotating the annular housing, the pinion including a web that is securely connected to the hollow shaft and to the inner and outer annular walls; radial oil outlets in the outer wall; and oil-free air outlets in the inner wall. The axial mixture inlets and the radial oil outlets are axially arranged on either said of the web to prevent the axial mixture inlets from reintroducing oil evacuated by radial oil outlets into the enclosure annular housing.

Abstract: The disclosure relates to a system for deoiling an air-oil pressurizing mixture for pressurized enclosures of a turbine engine. The system includes at least one centrifugal degasser, at least one mechanical casing of the turbine engine comprising a plurality of mechanical parts, at least one of which is mechanically connected to a drive shaft of the degasser so as to be able to rotate same. The casing is configured to contain an oil mist for lubricating the mechanical parts. The deoiling system also comprises means for isolating the air-oil mixture from the oil mist of the mechanical casing so that the oil mist of the mechanical casing cannot enrich with oil the mixture to be separated by the degasser.

Abstract: The invention relates to a centrifugal deaerator for an air/oil mixture of a turbomachine, comprising: an annular housing (10) for the centrifugal separation of said mixture, arranged around a hollow shaft (11); axial inlets (14) for the flow of said air/oil mixture into said housing (10); a pinion (20) for rotating said housing (10); and radial oil outlets (15) and oil-free air outlets (16), characterised in that it comprises a metal foam (50) housed in said housing (10) by partially extending along the axial direction (XX?) so as to define two successive spaces, a foam-free space (51) and a foam-lined space (52), said foam-free space opening up towards said axial inlets. A device can be advantageously added to the hollow shaft in order to reduce the free-vortex phenomenon and to thereby significantly reduce the load losses of the deaerator.

Abstract: The invention relates to an aircraft wing including two members removably connected end to end by a coupling including: a male coupling part with spaced opposed upper and lower faces, a first face being planar while the second face has a longitudinal relief (9) with a V-shaped section, the first and second faces being mutually included towards each other at their free ends; a female coupling part with spaced upper and lower faces facing each other, a first face being planar while the second face has a longitudinal relief with a V-shaped section complementary to that of the relief, and the first and second faces being mutually inclined away from each other at their free ends; and a fastener for retaining the two parts coupled with their respective interacting faces in a mutual bearing relation.

Abstract: The invention relates to an aircraft wing including two members removably connected end to end by a coupling means including: a male coupling part with spaced opposed upper and lower faces, a first face being planar while the second face has a longitudinal relief (9) with a V-shaped section, said first and second faces being mutually included towards each other at their free ends; a female coupling part with spaced upper and lower faces facing each other, a first face being planar while the second face has a longitudinal relief with a V-shaped section complementary to that of the relief, and said first and second faces being mutually inclined away from each other at their free ends; and means for retaining the two parts coupled with their respective interacting faces in a mutual bearing relation.