Bleed air systems for aircraft engines

An aircraft engine, comprising:

• an engine core including a compressor and a combustor downstream of the compressor relative to a gas flow through the engine core;
• a casing surrounding the engine core, the casing defining a bleed port downstream of an inlet of the compressor and upstream of the combustor relative to the gas flow;
• a bleed air system fluidly connected to the bleed port, the bleed air system having:
• a bleed air conduit fluidly communicating with the bleed port, the bleed air conduit defining a bleed passage for a bleed air flow;
• and
• a connector fluidly connecting the bleed port to the bleed air conduit, the connector 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 distributed at a plurality of axial locations along the connector axis between the port end and the conduit end of the connector, the connector having an upstream section located upstream of a plane normal to a central axis of the aircraft engine and intersecting the connector axis at the port end, and a downstream section located downstream of the plane relative to the gas flow through the engine core, the ribs located at least within the downstream section,
• wherein the ribs are configured to reduce acoustic and vibration responses of the bleed air conduit.