FIELD: transport.
SUBSTANCE: aircraft turbojet compressor (1) comprises grating (2) of fixed blades and air intake system at the level of passages (5) between two blades (3) via slits (6 made said wall (4). Blades (3) are fitted on wall (4) to make air passages (5) there between. Slits are arranged in a discrete manner to make multiple holes (O1, O2, O3, O4) located in airflow direction (E). Upstream hole (O1) of every slit (6) features cross-section area larger than that of the other, downstream, holes (O2, O3, O4) of slit (6). Quantity and cross-section of downstream holes (O2, O3, O4) can vary depending upon preset suction flow rate. This invention consists in the air intake at the level of passages between two blades effected by means of multiple holes arranged one after the other in airflow direction to substitute the sole hole. Suction distribution among several openings allows ruling out of recycling possible in sole hole.
EFFECT: decreased secondary losses in impeller and ruled out flow separation.
8 cl, 4 dwg
