A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle (501) defining a duct (502), and a fan (503) located within the duct. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (rhub) to a tip defining a 100 percent span position (rtip) and a plurality of span positions therebetween (r ∈ [rhub, rtip]). A hub-tip ratio of the fan, defined as the ratio of the diameter of the hub to the diameter of the fan measured at the leading edge of the blades, is from 0.45 to 0.55.
BOUNDARY LAYER INGESTION FAN SYSTEM
GRENZSCHICHTAUFNAHMEGEBLÄSESYSTEM
SYSTÈME DE VENTILATEUR D'INGESTION DE COUCHE LIMITE
2022-01-12
Patent
Electronic Resource
English