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 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]). The hub has a negative hade angle (γ) with respect to the rotational axis at an axial position coincident with the leading edge of the blades.
BOUNDARY LAYER INGESTION FAN SYSTEM
GRENZSCHICHTAUFNAHMEGEBLÄSESYSTEM
SYSTÈME DE VENTILATEUR D'INGESTION DE COUCHE LIMITE
2021-06-30
Patent
Electronic Resource
English