A flushing method for a lubricating oil system includes a step of performing precedent inside oil flushing for bearing box, by connecting an oil supply pipe and a flushing apparatus mounted to a bearing box to each other by a bypass pipe while bypassing an internal pipe that is provided in the bearing box and introduces an oil supplied from the oil supply pipe to a part between a rotor of a turbine and a bearing, supplying the oil from the oil supply pipe to the flushing apparatus through the bypass pipe, and injecting the oil from the flushing apparatus into the bearing box, to thereby perform oil flushing for the inside of the bearing box; and a final oil flushing step of supplying the oil from the oil supply pipe to an internal pipe, to thereby perform oil flushing for the inside of the lubricating oil system, after the step of performing precedent inside oil flushing for bearing box.

An evaluation of the oil level of an aircraft engine tank from doses of oil delivered from another tank by a pump can be checked by comparing the evaluation of the volume provided by a sensor associated with the engine tank with an estimation of the volume extracted from the aircraft rank, either by another level sensor associated with this tank, or directly from the control of the pump. This comparison is made by a module capable of notifying staff of the need to check or maintain the device, and in particular to check if the sensor is operating correctly. Application to aeronautics, in particular to devices wherein a single aircraft tank supplies all the engine tanks.

A lubricant filler for a lubricant tank of an aircraft engine comprises a filler tube having an upper portion to be disposed outside the volume of the tank and a lower portion to be disposed inside the volume. First and second openings are respectively provided in the upper and lower portions. An oil volume sensor is received in the filler tube through the first opening. A valve is connected to the filler tube and movable between an open position in which the valve provides a fluid connection into the lower portion via the second opening, and a closed position in which the valve blocks the fluid connection into the lower portion via the second opening. A third opening, smaller than both the first and second openings, defined one of: a) through a sidewall of the lower portion of the filler tube to provide a fluid connection between the volume and the lower portion when the lubricant filler assembly is attached to the lubricant tank, and b) through the valve to provide the fluid connection when the lubricant filler assembly is attached to the lubricant tank.

A bearing chamber housing for supporting a shaft of a turbomachine is provided, the bearing chamber housing including an additively built-up housing wall which bounds an oil chamber of the bearing chamber housing radially outwardly relative to an axis of rotation of the shaft, the housing wall being built up with an oil duct which has an inlet opening toward the oil chamber for admission of oil from the oil chamber into the oil duct, and which has an outlet opening for discharging the oil from the oil duct, the outlet opening being located at a different axial position and at a different circumferential position than the inlet opening, considered relative to the axis of rotation of the shaft, and the oil duct having an extent with both an axial component and a circumferential component, at least over a portion thereof.

A bearing chamber housing for supporting a shaft of a turbomachine is provided, the bearing chamber housing including an additively built-up housing wall which bounds an oil chamber of the bearing chamber housing radially outwardly relative to an axis of rotation of the shaft, the housing wall being built up with an oil duct which has an inlet opening toward the oil chamber for admission of oil from the oil chamber into the oil duct, and which has an outlet opening for discharging the oil from the oil duct, the outlet opening being located at a different axial position and at a different circumferential position than the inlet opening, considered relative to the axis of rotation of the shaft, and the oil duct having an extent with both an axial component and a circumferential component, at least over a portion thereof.

An impeller (230) for a planet carrier of a planetary gear speed reducer of a turbomachine, is configured intended to be rotatably secured to the planet carrier and to be rotated about an axis A of the speed reducer. The impeller has an annular shape about the axis and includes lubrication means (43, 45, 238), in particular for lubricating bearings of planet gears of the speed reducer. The lubrication means include an annular cavity (238) situated at the inner periphery of the impeller. The impeller includes an inner peripheral wall (246) closing the cavity (238) in the radial direction, and the impeller includes an annular port (248) that extends around the axis and that opens in the axial direction into the cavity in order to supply it with lubricating oil.

An impeller (230) for a planet carrier of a planetary gear speed reducer of a turbomachine, is configured intended to be rotatably secured to the planet carrier and to be rotated about an axis A of the speed reducer. The impeller has an annular shape about the axis and includes lubrication means (43, 45, 238), in particular for lubricating bearings of planet gears of the speed reducer. The lubrication means include an annular cavity (238) situated at the inner periphery of the impeller. The impeller includes an inner peripheral wall (246) closing the cavity (238) in the radial direction, and the impeller includes an annular port (248) that extends around the axis and that opens in the axial direction into the cavity in order to supply it with lubricating oil.

The invention relates to a device for connecting parts of an aircraft engine. The connection device comprises connectors suitable for connecting a first and a second part so as to establish a physical transfer link between these parts and means which enable it to monitor the state of the connection in particular by means of an impedance measurement carried out in a circuit formed by components integrated into said connectors.

The invention relates to a device for connecting parts of an aircraft engine. The connection device comprises connectors suitable for connecting a first and a second part so as to establish a physical transfer link between these parts and means which enable it to monitor the state of the connection in particular by means of an impedance measurement carried out in a circuit formed by components integrated into said connectors.

Turbine engine assembly comprising: an external casing (28) of a low-pressure compressor (4), an annular wall (30) and an oil tank (46) with a circular chamber (48) around an axis (14) of the compressor. The wall (30) comprises an inner surface (38) delimiting an primary guide path for the flow of the compressor, and an external surface (40) radially opposite the inner surface and delimiting the internal chamber (48) of the tank (46).