US 12,006,055 B2
Gas turbine engine with electric machines
Benjamin J Sellers, Bath (GB); Andrew J Newman, Bristol (GB); Gordon Margary, Bristol (GB); Paul R Davies, Bristol (GB); and Stephen J Bradbrook, Clevedon (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Sep. 8, 2022, as Appl. No. 17/940,030.
Claims priority of application No. 2112774 (GB), filed on Sep. 8, 2021.
Prior Publication US 2023/0219694 A1, Jul. 13, 2023
Int. Cl. B64D 33/08 (2006.01); B64D 27/02 (2006.01)
CPC B64D 33/08 (2013.01) [B64D 27/026 (2024.01)] 13 Claims
OG exemplary drawing
 
1. 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),
the heat exchanger being 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 through a duct towards a fan where the airflow separates into a core engine flow and a bypass flow downstream of the fan, wherein the duct is elongated and positioned upstream of the fan, and the heat exchanger comprises a plurality of heat transfer elements extending radially outwardly from a central hub along an axis of rotation of the gas turbine engine, and
wherein, when the gas turbine engine is operating at a full power condition at Sea Level Static conditions and in an International Standard Atmosphere of 15° C. and 1,013.25 mb, a ratio S of:

OG Complex Work Unit Math
is between 0.50 and 5.00.