Combination of a gas turbine engine and a power electronics

A combination of a gas turbine engine and power electronics for powering aircraft and/or engine systems, wherein

• the engine includes:
• an engine core comprising a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor;
• and
• a fuel circuit for supplying a fuel flow to the combustor;
• the fuel circuit includes:
• a fuel tank;
• a low pressure pump arranged downstream of the fuel tank and configured to pressurise fuel to a low pressure;
• a high pressure pump configured to receive the low pressure fuel and increase the pressure to a high pressure for onward supply to a fuel metering system;
• a loop configured to circulate a portion of the low pressure fuel in the loop during selected engine conditions;
• a phase change material located on the loop, such that the portion of the low pressure fuel transfers heat from the power electronics to the phase change material, the phase change material having a phase change temperature at a predetermined limiting temperature whereby the phase change material stores heat from the portion of the low pressure fuel, which prevents the power electronics from exceeding the limiting temperature;
• a cooling pump on the loop configured to drive only the portion of the low pressure fuel;
• and
• the loop is formed downstream of an outlet of the low pressure pump and upstream of an inlet of the high pressure pump.