Abstract: A bushing for a variable set blade includes a cylindrical part configured to receive the blade, the root of the blade being able to rotate in the cylindrical part, and a base including: a first side able to be put in contact with a first edge of a circumferential groove of the ring, and/or a second side able to be put in contact with a second edge of the circumferential groove of the ring. At least one of the first side or second side of the base includes at least one bevel through which the first side or the second side is able to be put in contact with one of the first edge or second edge of the circumferential groove so as to block the bushing in rotation. The invention finds a particularly interesting application in the field of aircraft.

Abstract: A bushing for a variable set blade includes a cylindrical part configured to receive the blade, the root of the blade being able to rotate in the cylindrical part, and a base including: a first side able to be put in contact with a first edge of a circumferential groove of the ring, and/or a second side able to be put in contact with a second edge of the circumferential groove of the ring. At least one of the first side or second side of the base includes at least one bevel through which the first side or the second side is able to be put in contact with one of the first edge or second edge of the circumferential groove so as to block the bushing in rotation. The invention finds a particularly interesting application in the field of aircraft.

Abstract: This object is achieved by the bleed-off means comprising means for tapping air from the primary duct which are arranged upstream of the intermediate casing and means for evacuating the air tapped into the secondary duct downstream of the support arms, these means comprising conduits arranged around the intermediate casing under the platforms.

Abstract: The invention relates to a bypass turbojet comprising a primary duct, a secondary duct, a low-pressure compressor, a high-pressure compressor, and a structural intermediate casing arranged axially between said low-pressure compressor and said high-pressure compressor, said intermediate casing being equipped at its periphery with a plurality of support arms having platforms which internally delimit the secondary duct, in which bleed-off means are provided, allowing some of the gaseous stream delivered by the low-pressure compressor to be tapped off and led to the secondary duct. Said bleed-off means comprise means for tapping air from said primary duct which are arranged upstream of said intermediate casing and means for removing the air tapped from said secondary duct downstream of said support arms, these means comprising conduits arranged around said intermediate casing under said platforms.

Abstract: A stator suitable for high-pressure compressors in gas turbine engines includes two points of ventilation at different temperatures. It is recommended that the upstream section of the stator be constructed with a casing and a shroud, both of which are unbroken around a circumference and made of a material with a low degree of thermal expansion. Downstream the shroud is, however, constructed using angular sectors in a material with a higher degree of thermal expansion.