Inner Shroud Sector For An Aircraft Turbomachine

Abstract: The invention relates to an inner shroud sector (1) configured to internally delimit a secondary duct (41) of an aircraft turbomachine (50) the inner shroud sector (1) comprising a downstream end (2) which comprises an upstream longitudinal portion (3) and a downstream longitudinal portion (4) which are connected by a middle portion (5) and are configured to extend respectively in the upstream extension and internally to a nacelle inner casing (31) the inner shroud sector (1) comprising an inner layer and an outer layer of composite material the middle portion (5) of the downstream end (2) comprising at least one volume of intumescent material sandwiched between the inner layer and the outer layer of the composite material so as to form a local thickened portion in the longitudinal direction.

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