Abstract: An oil tank for a turbomachine provided with a probe for measuring the oil level. The probe may be a capacitive electrical probe, introduced into the tank so as to be arched. A sleeve encircles lamellar electrodes of the probe to guide the probe during its mounting in the tank and to hold the electrodes in position. A method of mounting the probe in a tank.

Abstract: 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.

Abstract: 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.

Abstract: A lubrication assembly includes two pumps whose shafts are coupled for rotation via at least one polygonal profile coupling.

Abstract: A fluid pump for an aircraft turbomachine includes a ring through which a duct passes along a central axis, a rotor driven in rotation with respect to the ring along a main axis offset relative to the central axis. Cavities between the ring and the rotor have volumes that vary according to the angular position of the rotor with respect to the ring. The pump further includes an inlet space for admitting the fluid into the cavities and a discharge space for discharging the fluid from the cavities, the pressure in the discharge space being higher than the pressure in the inlet space. A groove pressurizes the cavities in the discharge space when the rotor rotates.

Abstract: A combustion liner for a gas turbine engine. The combustion liner defines a bypass direction which extends between an upstream portion and a downstream portion of the combustion liner in use, the combustion liner. The combustion liner comprises a liner wall for defining at least a portion of a combustion chamber, the liner wall having an outer surface and an inner surface and a depth between the outer and inner surfaces of the combustion liner in use. The combustion liner comprises a chute formed through the liner wall for conveying fluid from the outer surface through the liner wall and ejecting fluid from an exhaust hole of the chute on the inner surface, the exhaust hole having a length L along the bypass direction.