FIELD: engines and pumps.
SUBSTANCE: gas turbine engine high-pressure compressor 10 comprises air bleeder. Gas turbine engine represents an aircraft turbojet or turboprop. Air bleeder comprises channel 58 with suction end extending into outer case 14 of compressor 10 at the level of impeller 18 and compressor straightener blade 24. Circular sheet board 62 is arranged inside said case opposite suction end of channel 58 to extend through less than 360 degrees. Said board 62 features L-shape cross-section.
EFFECT: uniform air bleeding, limited angular static pressure drops.
14 cl, 8 dwg
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