COMBINATION OF A GAS TURBINE ENGINE AND A POWER ELECTRONICS

The present invention provides a combination of a gas turbine engine and a power electronics for powering aircraft and/or engine systems. The engine includes an engine core and an oil circuit configured to cool and lubricate bearings of the engine core, and a fuel circuit for supplying fuel to the combustor. The fuel circuit includes a low pressure pump for pressurising the fuel to a low pressure, and a high pressure pump configured to receive the low pressure fuel and increase the pressure to a high pressure for supply to a fuel metering system and thence to the combustor. The engine also includes a fuel-oil heat exchanger having a fuel side on the fuel circuit between an outlet of the low pressure pump and an inlet of the high pressure pump, and an oil side on the oil circuit to transfer heat from the oil circuit to the fuel circuit. The power electronics is configured to transfer heat produced by the power electronics to a cooling flow formed by a portion of the low pressure fuel.