Patent ID: 11946417
Assignee: ROLLS-ROYCE PLC
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B  Y | IPC F

Claim 0:
1. A combination of a gas turbine engine and a-power electronics for powering aircraft and/or engine systems,
wherein the gas turbine engine includes:
an engine core comprising a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor;
an oil circuit configured to cool and lubricate bearings of the engine core;
a fuel circuit for supplying fuel to the combustor, the fuel circuit including:
a low pressure pump for pressurising the fuel to a low pressure; and
a high pressure pump configured to receive low pressure fuel from the low pressure pump and increase the pressure to a high pressure for supply to a fuel metering system and thence to the combustor; and

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; and
wherein 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 from the low pressure pump, the cooling flow being extracted from and returned to the fuel circuit between the outlet of the low pressure pump and the fuel side of the fuel-oil heat exchanger,
wherein the gas turbine engine further includes:
a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and
a bypass duct for a bypass airflow produced by the fan outside the engine core,
wherein the gas turbine engine further includes an air-cooled heat exchanger configured to transfer heat produced by the power electronics to an air flow produced by the gas turbine engine.