Patent ID: 11952945
Assignee: ROLLS-ROYCE PLC
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 10:
11. A method of operating a thermal management system for an aircraft, the thermal management system comprising a first gas turbine engine, a first heat exchanger, one or more first ancillary systems, one or more second ancillary systems, and a second heat exchanger;
wherein the method comprises the steps of:
(i) providing a first thermal bus comprising a first heat transfer fluid with the first heat transfer fluid providing fluid communication, in a closed loop flow sequence, between the first gas turbine engine, the first heat exchanger, and the or each first ancillary system;
(ii) transferring a waste heat energy generated by at least one of the first gas turbine engine, and the or each first ancillary system, to the first heat transfer fluid;
(iii) transferring a waste heat energy generated by the or each second ancillary system, being in a range of between 20 kW and 300 kW, to a second heat transfer fluid;
(iv) transferring a waste heat energy from the second heat transfer fluid to the first heat transfer fluid, using the second heat exchanger;
(v) providing a vapour compression system to increase a temperature of the second heat transfer fluid having passed through the or each second ancillary system to a value greater than a temperature of the first heat transfer fluid entering the second heat exchanger; and
(vi) transferring the waste heat energy from the first heat transfer fluid to a dissipation medium, using the first heat exchanger.