Gas turbine engine with bleed air removal device

摘要

The gas turbine engine has a compressor (13) and an air bleed device that is comprised of an annular channel (30) in a radially outer wall (31) of a flow channel (29). An annular sealing element (32) is arranged in the region of the annular channel, and is displaced from a closed position to an open position in an axial direction. The sealing element has an annular flow splitter projection (33) protruding in the flow channel in the open position. The flow channel is aligned in radial direction at an angle to a central axis of an engine at the area of the air bleed device.