Bleed air systems for aircraft engines

Abstract

An aircraft engine, has: an engine core including a compressor and a combustor; a casing defining a bleed port downstream of an inlet of the compressor and upstream of the combustor; a bleed air system connected to the bleed port and having: a bleed air conduit communicating with the bleed port and defining a bleed passage; and a connector connecting the bleed port to the bleed air conduit and extending from a port end at the bleed port to a conduit end at the bleed air conduit, the connector having a peripheral wall extending around a connector axis transversally intersecting the casing, the peripheral wall having an inner surface facing and exposed to the bleed passage, the inner surface defining ribs extending at least partially circumferentially around the connector axis, the ribs being axially distributed relative to the connector axis between the port end and the conduit end.