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.
OPTIMIZED GAS TURBINE ENGINE FOR AIRCRAFT
25.06.2020
Patent
Elektronische Ressource
Englisch
INLET CONE FOR AN AIRCRAFT TURBINE ENGINE AND ASSOCIATED AIRCRAFT TURBINE ENGINE
Europäisches Patentamt | 2022
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