Auxiliary oil tank for an aircraft turbine engine
An auxiliary tank for an aircraft turbine engine is provided, and in conjunction with a pump and associated auxiliary lubrication circuit, supplies oil to a reducer when, for example, a phase of free rotation of the fan is detected. Thus, the reducer is always lubricated, even during the phases of free rotation of the fan, thus ensuring a longer life of the reducer gears. The auxiliary tank is arranged with respect to the reducer so that oil is recovered from the reducer at least in part by the auxiliary tank.
1. A method of lubricating a reducer of an aircraft turbomachine, the aircraft turbomachine having a main tank and a main lubrication circuit configured to lubricate the reducer when the turbomachine is active and having an auxiliary tank and an auxiliary lubrication circuit configured to lubricate the reducer when the turbomachine is not active, the method comprising:
detecting a phase of free rotation of a fan of the turbomachine; and thereafter,
activating a pump associated with the auxiliary lubrication circuit so that oil is supplied to the reducer from the auxiliary tank, and
filling the auxiliary tank with oil recovered from the reducer when the turbomachine is active, and when the auxiliary tank is full, filling the main tank with oil that overflows from the auxiliary tank.
2. The method of claim 1 , further comprising
lubricating, via the main lubrication circuit, the reducer with oil when the turbomachine is active.
3. The method of claim 2 , further comprising
filling the auxiliary tank with oil from the main lubrication circuit when the turbomachine is active.
4. The method of claim 1 , wherein the reducer is connected in fluid communication with the auxiliary tank and the auxiliary lubrication circuit, and wherein the reducer is connected in fluid communication with the main lubrication tank and the main lubrication circuit.
5. The method of claim 1 , further comprising
recovering oil from the reducer into the auxiliary tank and into the main lubrication tank.
6. The method of claim 5 , wherein when the auxiliary tank is filled with oil recovered from the reducer, the oil overflows into a passage connected in fluid communication with the main lubrication tank.
7. A method of lubricating a reducer of an aircraft turbomachine, comprising:
lubricating, via a main lubrication circuit, the reducer when the turbomachine is active; and
lubricating, via an auxiliary lubrication circuit, the reducer when the turbomachine is not active, the main lubrication circuit comprising a main lubrication tank and the auxiliary lubrification circuit comprising an auxiliary lubrication tank,
filling the auxiliary tank with oil recovered from the reducer when the turbomachine is active, and when the auxiliary tank is full, filling the main tank with oil that overflows from the auxiliary tank.
8. The method of claim 7 , wherein the reducer is connected in fluid communication with the auxiliary tank and the auxiliary lubrication circuit, and wherein the reducer is connected in fluid communication with the main lubrication tank and the main lubrication circuit.
9. The method of claim 8 , further comprising
detecting a phase of free rotation of a fan of the turbomachine; and thereafter,
activating a pump associated with the auxiliary lubrication circuit so that oil is supplied to the reducer from the auxiliary tank.
10. A method of lubricating a reducer of an aircraft turbomachine having an auxiliary tank having a curved shape with a radius of curvature centered on a centering axis corresponding to a longitudinal axis of the turbomachine, the turbomachine further having a reducer, a main lubrication oil tank, a main lubrication circuit, an auxiliary lubrication circuit, and an oil outlet connected to a pump, the method comprising:
lubricating, via the main lubrication circuit, the reducer when the turbomachine is active; and
lubricating, via the auxiliary lubrication circuit, the reducer when the turbomachine is not active by activating the pump so that oil is supplied from the auxiliary tank to the reducer as soon as a phase of free rotation of a fan of the turbomachine is detected, and
filling the auxiliary tank with oil recovered from the reducer when the turbomachine is active, and when the auxiliary tank is full, filling the main tank with oil that overflows from the auxiliary tank.
11. The method of claim 1 , wherein the auxiliary tank has a curved shape with a radius of curvature centered on a centering axis corresponding to a longitudinal axis of the turbomachine, the auxiliary tank comprising:
a cylindrical or frustroconical radially outer wall,
three cylindrical or frustroconical radially inner walls arranged opposite said radially outer wall, and
an inner volume forming a U-shape enclosed by the radially outer wall and the radially inner walls.
12. The method of claim 11 , wherein the radially inner walls comprise a middle wall and two side walls arranged on either side of the middle wall, the middle wall has a mean radius of curvature greater than a mean radius of curvature of the two side walls.
13. The method of claim 12 , the U-shape of the inner volume has a base and a plurality branches, the plurality of branches are formed by lateral volume portions between the two side walls and the radially outer wall, and wherein the base is formed by a middle volume portion between the middle wall and the radially outer wall.