Bleed air extraction device for a gas turbine engine

A bleed air extraction device for a turbomachine, comprising:

• an axial compressor, formed in a flow path and having at least one compressor stage, which comprises a rotor and a stator, wherein the flow path is bounded radially on an inside by a radially inner flow path boundary and radially on an outside by a radially outer flow path boundary,
• a bleed air duct configured to guide a bleed air flow branched off from the flow path of the axial compressor, wherein the bleed air duct includes:
• an inlet opening, which is formed downstream of the rotor or the stator of the axial compressor in the radially outer flow path boundary,
• an axially forward wall adjoining the inlet opening, and
• an axially rearward wall adjoining the inlet opening,
• a guide mechanism configured to guide at least a portion of the bleed air flow increasingly in a direction of the axially forward wall of the bleed air duct;
• the guide mechanism including flow-guiding bodies shaped as ribs and positioned on the axially rearward wall of the bleed air duct, the ribs being aligned in the longitudinal direction of the bleed air duct and deflecting the bleed air flow in the bleed air duct increasingly in the direction of the axially forward wall of the bleed air duct, wherein the ribs extend from the axially rearward wall only partially into the bleed air duct and do not extend to the axially forward wall.