Arrangement for a tank between a nacelle cowling and a turbomachine
View Patent ↗An arrangement of a tank of lubrication liquid for an aircraft turbomachine, under a nacelle cowling covering the turbomachine, is provided. The tank is arranged in the volume located between the turbomachine and the nacelle cowling. The nacelle cowling includes an opening for access to the volume. The tank is fastened to an internal face of a panel closing off the opening. The unit formed by the panel and the tank is added onto the nacelle cowling and is able to be mounted and dismounted from the nacelle cowling.
1. An arrangement of a tank of lubrication liquid of an aircraft turbomachine, under a nacelle cowling covering said aircraft turbomachine, with the tank being arranged in a volume located between the aircraft turbomachine and the nacelle cowling, with the nacelle cowling comprising an opening for access to said volume,
wherein the tank is fastened to an internal face of a panel that closes off said opening ( 22 ), with a unit formed by the panel and the tank being added onto the nacelle cowling and able to be mounted and dismounted from the nacelle cowling.
2. The arrangement as claimed in claim 1 , wherein the tank and the panel are made of a single part.
3. The arrangement as claimed in claim 1 , wherein the panel forms a wall of the tank.
4. The arrangement as claimed in claim 1 , wherein the panel comprises an opening which provides access an orifice for filling the tank.
5. The arrangement as claimed in claim 1 , wherein the tank comprises a wall which is attached to the internal face of the panel.
6. The arrangement as claimed in claim 5 , wherein said wall of the tank comprises a device for visually checking an oil level in the tank and the panel comprises an opening located facing said device for visually checking.
7. The arrangement as claimed in claim 1 , wherein the tank comprises an electronic sensor for measuring an oil level and an electrical connector for connecting the electronic sensor to an electronic device for managing the aircraft turbomachine, said electrical connector being located at a distance from the electronic sensor.
8. The arrangement as claimed in claim 1 , wherein the aircraft turbomachine is of a main horizontal axis and the nacelle cowling comprises an upper portion and a lower portion, wherein the tank and the panel are fastened to the upper portion of the nacelle cowling.
9. The arrangement as claimed in claim 1 , wherein the tank comprises an oil outlet connector and an oil return connector of a self-closing type.