Gas turbine engine

A gas turbine engine for an aircraft comprising:

• an engine core comprising at least one turbine, at least one compressor and at least one shaft connecting the turbine to the compressor;
• a fan located upstream of the engine core, the fan comprising a plurality of fan blades;
• a unit supplied with oil from a first oil circuit and at least a second oil circuit;
• the first oil circuit and the second oil circuit each are fluidly coupled with at least one inlet and with at least one outlet of the unit and with at least one inlet and with at least one outlet of an oil tank;
• the first oil circuit and the second oil circuit configured to receive oil from the oil tank and to direct the received oil to the unit;
• the oil tank incorporating offset outlets to each of the oil circuits;
• and
• the offset outlet of the second oil circuit positioned higher in the oil tank than the offset outlet of the first oil circuit.