An gas turbine engine for an aircraft includes, in axial flow sequence, a compressor module, a combustor module, and a turbine module, together with a first electrical machine rotationally connected to the turbine module. The combustor module has a combustor volume V (cm3). In use, at a full power condition, the gas turbine engine has a maximum corrected core flow Q (m3/sec), and a ratio T of:T=(MaximumCorrectedCoreFlow=Q)(Combustorvolume=V)is in a range of between 450 and 2,500.
Improved gas turbine engine
2023-06-15
Patent
Elektronische Ressource
Englisch