Patent ID: 11268450

Abstract:
A turbomachine comprising a ducted fan, a low-pressure turbine shaft and a reduction gearbox housed in a casing between the fan and the low-pressure turbine shaft, the fan rotor supplying airflow to a primary stream and a secondary stream and comprising a hub of diameter D1, wherein—the diameter D3 of the fan rotor is greater than 82 inches (2.08 metres), —the pressure ratio of the fan is between 1.10 and 1.35, the turbomachine comprises a low-pressure compressor separate from the fan, the reduction gearbox being interposed between the fan rotor and a turbine shaft of the low-pressure compressor, and wherein the reduction gearbox casing has an outside diameter D2 greater than the diameter D1 of the hub, the pitch diameter D4 of the reduction gearbox ring being between 0.15 and 0.35 times the fan rotor diameter.