The present application provides a gas turbine engine (10) for an aircraft and an aircraft, the gas turbine engine being arranged below a wing (52) of the aircraft and comprising an engine core (11) comprising a turbine (19), a compressor (14) and a mandrel (26) connecting the turbine to the compressor, said turbine (19) comprising a lowest pressure rotor stage (19b) and having a turbine diameter(122); a fan (23) located upstream of the engine core (11), the fan comprising a plurality of fan blades (64) extending from a hub (66); and a gearbox (30) that receives input from the mandrel (26) and outputs a drive to the fan (23) so as to drive the fan at a lower rotational speed than the mandrel. The downstream blocking ratio is in the range of 0.2 to 0.3.
Turbine engine
2019-02-06
Patent
Elektronische Ressource
Englisch