Onboard system and a method for draining an aeroengine
An onboard system and a method for draining an aeroengine. The onboard system comprises a buffer tank having an admission passage for admitting under gravity fluid coming from the aeroengine, a primary tank situated above the buffer tank and having an emptying passage for emptying the fluid coming from the aeroengine, and a lift circuit connecting the buffer tank to the primary tank in order to transfer the fluid coming from the aeroengine from the buffer tank to the primary tank.
1. A propulsion unit comprising:
an aeroengine; and
an onboard system for draining the aeroengine, the onboard system comprising:
a buffer tank situated below the aeroengine and including an admission passage for admitting fluid coming from the aeroengine under gravity;
a primary tank situated above the buffer tank and including an emptying passage for emptying the fluid coming from the aeroengine; and
a lift circuit connecting the buffer tank to the primary tank in order to transfer the fluid coming from the aeroengine from the buffer tank to the primary tank; and
a suction device connected to the primary tank, wherein the suction device comprises a pneumatic chamber in a suspension of a landing gear that is connected to the primary tank.
2. The propulsion unit according to claim 1 , wherein the lift circuit includes a pump between the buffer tank and the primary tank.
3. The propulsion unit according to claim 2 , wherein the pump between the buffer tank and the primary tank is an electrically driven pump.
4. The propulsion unit according to claim 2 , wherein the pump between the buffer tank and the primary tank is a Venturi effect pump.
5. The propulsion unit according to claim 1 , further comprising a pressurizing device for pressurizing the buffer tank.
6. The propulsion unit according to claim 1 , wherein the primary tank is situated above the aeroengine.
7. The propulsion unit according to claim 1 , further comprising a pressurizing device connected to the aeroengine, wherein the pressurizing device comprises a valve and a pressurizing duct.
8. A method of draining an aeroengine, the method comprising:
admitting fluid coming from the aeroengine into a buffer tank situated below the aeroengine, the fluid being admitted by gravity through a feed passage of the buffer tank;
sucking the fluid via a lift circuit from the buffer tank to a primary tank situated above the buffer tank, using a suction device connected to the primary tank, wherein the suction device comprises a pneumatic chamber in a suspension of a landing gear that is connected to the primary tank; and
emptying the fluid via an emptying passage of the primary tank.