SYSTEME D'ECHAPPEMENT POUR COMPRESSEURS DE MOTEURS A TURBINE A GAZ

摘要

1319348 Axial-flow compressors GENERAL ELECTRIC CO 24 Sept 1970 [30 Sept 1969] 45540/70 Heading F1C When stall is incipient in a gas turbine engine compressor, a number of actuators 40 move a segmented ring 36 axially from the dash line position in which it closes a circumferential port 32, to the position shown in which it allows air to bleed from the compressor. The inner surface of the ring 36 and the co-operating surfaces at each side of the port 32 are tapered as shown to enhance sealing when the ring closes the port 36. The ring has a number of circumferentiallyspaced pads 48 which slidingly co-operate with guide ribs 50 on the compressor casing.