SAFRAN AERO BOOSTERS

A method for determining a lay-up geometry for creating a component made of composite material, includes a body which is a volume of revolution of axis directed in an axial direction, the body extending around the axial direction in a circumferential direction, and a flange extending from one end of the body in a direction of extension, the method involving determining a first surface having the shape of the body that is to be produced and determining a second surface, situated in the prolongation of the first surface, the second surface having closed curves of undulation in the circumferential direction, wherein the second surface also has corrective curvatures in the direction of prolongation.

A process for orbital friction welding of a blade to a stub on a turbomachine rotor disk, comprising the following successive phases: friction of the blade against the stub with application of a force friction normal; forging of the blade against the stub with application of a normal forging force; wherein the normal forging force is greater than the normal friction force and essentially constant throughout the forging phase.

An oil tank for an aircraft turbomachine, including: a main enclosure capable of containing the oil, an oil inlet mixed with air, an oil outlet, an auxiliary enclosure arranged inside the main enclosure, including an enclosing wall, and two end walls adjacent to the enclosing wall, at least one of the two end walls including at least one oil passage with the interior of the main enclosure, at least one auxiliary inlet opening tangentially to the enclosing wall and passing through the main enclosure, an auxiliary outlet, tangential to a larger diameter section of the surrounding wall. The auxiliary outlet passes through the main enclosure for connection to the auxiliary circuit.

An assembly for a turbomachine including a wall including a guide surface for an airflow and a row of stator blades extending from the wall and arranged annularly around an axis. The surface being inclined relative to the axis. The row of blades includes first blades extending substantially perpendicular to the axis and second blades extending substantially perpendicular to the guide surface. An axial turbomachine including a low-pressure compressor, a high-pressure compressor, and a swan-neck vein arranged axially between the low-pressure compressor and the high-pressure compressor. The swan-neck vein contains the assembly as described above.

A stage for a turbomachine compressor including a row of stator vanes extending radially inwards from an outer shell to an inner shell housed in a cavity of the rotor, and an air recirculation passage in the cavity, with an air inlet downstream of the inner shell and an air injection outlet between a face guide and an opposite guiding face upstream of the cavity, having profiles inclined radially downstream, relative to a perpendicular to an axial direction. The air injection outlet has a distance greater than or equal to one fifth of a common length, and the air recirculation passage in the cavity is devoid of a device for sealing upstream of the air inlet.

An air/oil heat exchanger arranged in a vein. The exchanger includes internal parietal corridors and/or external parietal corridors and central corridors, the radial height of the internal and/or external parietal corridors increasing from the inlet of the exchanger to its outlet.

A stator assembly including an upstream blade and a downstream blade axially overlapping and defining between them a channel. The inlet surface of the channel is greater than or equal to the outlet surface of the channel, preferably with a factor of 2. A turbomachine provided with such an assembly, arranged upstream of a high-pressure compressor.

A method for determining a draping geometry for producing a composite material part including a body being a volume of revolution with an axis directed along an axial direction having a given reference radius, the body extending around the axial direction along a circumferential direction, and a flange extending from one end of the body along a direction of extension, the method including determining a first surface having a radius smaller than the reference radius, and determining a second surface located in the extension of the first surface, the second surface having circumferential corrugation curves in the circumferential direction and in the direction of extension.

An oil tank for an aircraft turbomachine, including: a main enclosure capable of containing the oil, an oil inlet mixed with air, an oil outlet, an auxiliary enclosure arranged inside the main enclosure, including an enclosing wall, and two end walls adjacent to the enclosing wall, at least one of the two end walls including at least one oil passage with the interior of the main enclosure, at least one auxiliary inlet opening tangentially to the enclosing wall and passing through the main enclosure, an auxiliary outlet, tangential to a larger diameter section of the surrounding wall. The auxiliary outlet passes through the main enclosure for connection to the auxiliary circuit.

An air/oil heat exchanger arranged in a vein. The exchanger includes parietal corridors and central passages, the radial height of the parietal corridors is less than the radial height of the central corridors at the inlet of the exchanger.