Auxiliary oil tank for an aircraft turbine engine
An auxiliary tank for an aircraft turbine engine has a curved general shape, and includes a cylindrical or frustoconical radially outer wall and three cylindrical or frustoconical radially inner walls arranged facing the radially outer wall, the three radially inner walls having a middle wall and two side walls arranged to either side of the middle wall. The inner volume of the tank forms a U-shape, the branches of which are formed by lateral volume portions between the side walls and the radially outer wall, and the base of which is formed by a middle volume portion between the middle wall and the radially outer wall.
1. An auxiliary tank for an aircraft turbomachine having 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 frustoconical radially outer wall and three cylindrical or frustoconical radially inner walls arranged opposite said radially outer wall, the three radially inner walls comprising a middle wall and two side walls arranged on either side of the middle wall, the middle wall having a mean radius of curvature greater than a mean radius of curvature of said two side walls so that an inner volume of the auxiliary tank forms a U-shape having a base and a plurality of branches, wherein each of 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.
2. The auxiliary tank according to claim 1 , further comprising an oil inlet located on the middle wall.
3. The auxiliary tank according to claim 1 , wherein the lateral volume portions are connected to a plurality of gas outlets.
4. The auxiliary tank according to claim 1 , further comprising an oil outlet connected by a hose to a pump powered by an electric motor.
5. A casing for a turbomachine, comprising two coaxial annular walls, one of the two coaxial annular walls forming an inner casing of the turbomachine, extending inside the other of the two coaxial annular walls, forming an inter-duct casing of the turbomachine, and connected together by an annular row of arms configured to be swept by a flow of gas during operation, at least one of the arms of the annular row of arms being hollow and comprising a first inner passage configured for oil recovery and a second inner passage configured for oil recovery and for conveying oil to the auxiliary tank according to claim 4 .
6. The casing according to claim 5 , wherein said first and second inner passages are formed in the inter-duct casing and are formed by two channels separated by a partition and arranged side by side in a same plane passing through an axis of revolution of the inner casing and of the inter-duct casing.
7. The casing according to claim 5 , wherein the inter-duct casing comprises two radially outer annular rims between which the auxiliary tank is mounted.
8. The casing according to claim 5 , wherein the middle wall of the auxiliary tank is located perpendicularly to said at least one of the arms and the side walls are located perpendicularly to a plurality of inter-arm spaces.
9. An aircraft turbomachine comprising a casing according to claim 5 .
10. The aircraft turbomachine according to claim 9 , further comprising a reducer, a main lubrication oil tank and a main lubrication circuit, an auxiliary oil tank, and an auxiliary lubrication circuit, the auxiliary tank being connected to the reducer via the second inner passage, the main tank and the main lubrication circuit being configured to lubricate the reducer when the turbomachine is active, and the auxiliary tank and the auxiliary lubrication circuit being configured to lubricate the reducer when the turbomachine is not active.