Patent ID: 6938407

Claim:
A bypass turbojet comprising: a primary duct; a secondary duct; a low-pressure compressor; a high-pressure compressor; a structural intermediate casing arranged axially between said low-pressure compressor and said high-pressure compressor, said structural intermediate casing comprising a radial flange defining an upstream face of said structural intermediate casing, said structural intermediate casing being equipped at its periphery with a plurality of support arms having platforms which internally delimit the secondary duct, and bleed-off means allowing some of a gaseous stream delivered by said low-pressure compressor to be tapped off and led to said secondary duct, said bleed-off means comprising: means for tapping air from said primary duct, said means for tapping being arranged upstream of said radial flange of said intermediate casing, and means for evacuating said tapped air into said secondary duct downstream of said support arms, said means for evacuating comprising conduits arranged around said structural intermediate casing under said platforms.