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AssigneeROLLS-ROYCE plc
InventorsBenjamin J Sellers, Andrew J Newman, Gordon Margary, Paul R Davies, Stephen J Bradbrook
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A cooling system for an aircraft comprises a gas turbine engine, an ancillary apparatus, and a heat exchanger. The gas turbine engine comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate an electrical power PEM1 (W). The heat exchanger is configured to transfer a total waste heat energy Q (W) generated by the gas turbine engine and the ancillary apparatus, to an airflow passing through the heat exchanger, and a ratio S of: S = ( Total Electrical Power Generated = P EM 1 ) ( Total Heat Energy Rejected to Airflow = Q ) is in a range of between 0.50 and 5.00.
A cooling system for an aircraft, the cooling system comprising a gas turbine engine, an ancillary apparatus, and a heat exchanger, the gas turbine engine comprising, in axial flow sequence, the heat exchanger, a compressor module, a combustor module, and a turbine module, and a first electric machine being rotationally connected to the turbine module, the first electrical machine being configured to generate an electrical power PEM1 (W),
A method of operating a cooling system for an aircraft, the method comprising:
Dependencies are inferred from the claim text.