Cooling system for an internal partition of an air intake for an aircraft nacelle and associated method

Abstract

An air inlet (1) for an aircraft nacelle comprising an inner radial wall (11) and an outer radial wall (12) extending around a longitudinal axis (X) oriented from upstream to downstream and connected upstream by a leading edge (13), together forming an outer shell (10), an inner partition (2) fixed on one side to the inner radial wall (11) and on the other side to the outer radial wall (12) and defining with the outer shell (10) an annular chamber (3), the inner partition (2) comprising an upstream face (21) oriented towards the annular chamber (19) and a downstream face (22) opposite the upstream face (21), a de-icing duct (4) for injecting a de-icing airflow (DF) into the annular chamber (3), a cooling system (5) for the inner partition (2) configured to achieve forced circulation of a cooling airflow (FR) on the downstream face (22) of the internal septum (2). Figure from the abstract: Figure 2