Aeronautical engine with cooling of an electric starting device
View Patent ↗An aeronautical engine including a fuel pumping device including a high pressure fuel pump including an inlet connected to a low pressure fuel conduit and an outlet connected to a main circuit for feeding high pressure fuel, an electric device starting the engine, and a device cooling the electric starting device connected to the pumping device to ensure cooling by circulation of fuel. The cooling device is supplied with fuel by a pump that includes an inlet connected to the pumping device, upstream from the high pressure pump, and that is driven by an electric motor independently of the high pressure pump.
1. An aeronautical engine comprising:
a pumping device including a low pressure pump and a high pressure pump, an inlet of the high pressure pump connected to an outlet of the low pressure pump via a low pressure fuel conduit and an outlet of the high pressure pump connected to a main fuel circuit for feeding high pressure fuel to a combustion chamber of the engine;
an electric starting device to start the engine; and
a cooling device of the electric starting device connected to the pumping device to ensure cooling of the electric starting device by circulation of a heat transfer fluid, wherein the heat transfer fluid is oil, the cooling device including
a heat exchanger,
a heat transfer fluid circuit which circulates the heat transfer fluid through the electric starting device and the heat exchanger,
a cooling fuel circuit distinct from the main fuel circuit for feeding high pressure fuel, in fluid communication with the low pressure fuel conduit of the pumping device and which circulates the fuel through the heat exchanger into a tank, and
an electric pump driven by an electric motor, the electric pump being disposed in the cooling fuel circuit, the electric pump including an inlet connected to the low pressure fuel conduit of the pumping device, downstream of the low pressure pump and upstream from the high pressure pump, and the electric pump including an outlet in direct fluid communication with an inlet of the heat exchanger,
wherein a controller of the electric motor is configured to operate the electric motor independently of the high pressure pump such that the fuel circulates through the heat exchanger into the tank via the cooling fuel circuit during operation of the electric pump and to stop operation of the electric pump when a speed of a turbine shaft of the engine is greater than a predetermined value, and
wherein the low pressure pump circulates the fuel through the heat exchanger and into the tank via the cooling fuel circuit for cooling the heat transfer fluid and consequently cooling the electric starting device when the speed of the turbine shaft of the engine is greater than the predetermined value.
2. An aeronautical engine according to claim 1 , wherein the electric pump feeding the cooling device includes an outlet connected to the main fuel circuit for feeding high pressure fuel.
3. An aeronautical engine according to claim 2 , wherein the high pressure pump is a centrifugal pump.
4. An aeronautical engine according to claim 2 , wherein an anti-return valve is provided in a conduit connecting the outlet of the electric pump to the main fuel circuit for feeding high pressure fuel.
5. An aeronautical engine according to claim 1 , wherein the cooling device is configured to cool an electric starter of the electric starting device and an electronic circuit controlling power of the electric starter.
6. An aeronautical engine according to claim 1 , wherein the heat transfer fluid circuit includes a first conduit which brings the heat transfer fluid into circulation channels provided in a wall of a case of the electric starting device and a second conduit which recovers the heat transfer fluid circulated in the circulation channels and passes the recovered heat transfer fluid through the heat exchanger.