Aircraft gas turbine, has bleed air aperture that is opened into air conduit tube which is arranged within silencer element parallel to core thruster, where air conduit tube opens at end region of silencer element

摘要

The turbine has a core thruster (1) with a compressor arrangement (2) from which bleed air is withdrawn. A tubular silencer element (4) encloses the core thruster, and a by-pass channel (5) surrounds the silencer element. A bleed air aperture (3) of the compressor arrangement is opened into an air conduit tube (6) which is arranged within the silencer element parallel to the core thruster. The air conduit tube opens at an end region of the silencer element and tangential to the surface of the silencer element.