The utility model provides a gas turbine engine (10) for an aircraft and the aircraft. A gas turbine engine (10) for an aircraft has an engine length (110) arranged to be mounted below a wing (52) ofthe aircraft and comprising an engine core (11) comprising a turbine (19) comprising a lowest pressure rotor stage (19b), a compressor (14) and a mandrel (26); a fan (23) located upstream of the engine core, the fan having a fan tip radius (102); and a gearbox (30) that receives input from the mandrel (26) and outputs a drive to the fan so as to drive the fan at a lower rotational speed than the mandrel. The downstream blocking ratio is defined as: and the engine blocking ratio is in the range of 2.5 to 4.
Turbine engine
2019-02-06
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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