Abstract: A turbomachine comprising high- and low-pressure compressor shafts guided in bearings isolated from an internal enclosure by a sealing end plate, and radial pressurization tubes connecting the enclosure to an air passage passing through the intermediate casing, the ends of these tubes being engaged in sealed manner in radial ducts of the intermediate casing and in radial chimneys of the sealing end plate, the chimneys being of a length is sufficient to enable the ends of the tubes to be moved in translation therein between a service position and a mounting position for the tubes.

Abstract: A turbomachine comprising high- and low-pressure compressor shafts guided in bearings isolated from an internal enclosure by a sealing end plate, and radial pressurization tubes connecting the enclosure to an air passage passing through the intermediate casing, the ends of these tubes being engaged in sealed manner in radial ducts of the intermediate casing and in radial chimneys of the sealing end plate, the chimneys being of a length is sufficient to enable the ends of the tubes to be moved in translation therein between a service position and a mounting position for the tubes.

Abstract: Device for cooling the external part of a turbine disk (2) by means of an external fresh air current (circuit II) without mixing with the warmer ventilation from the center of the disk (circuit I). A part (30) through which ducts (31, 32) pass that intersect without interruption, prevents mixing of substantially perpendicular streams in front of a part (22) of the disk (2) and a mixture which reduces the cooling efficiency.

Abstract: A depressurization device for the lubrication chambers which surround the bearings of a turbomachine comprises venting ducts which communicate the lubrication chambers with the outside, and is provided with an auxiliary pumping mechanism which is arranged to be operated, when required, by way of an external pressure source. Preferably the venting ducts are provided with an air/lubricant separator and the auxiliary pumping mechanism comprises a jet nozzle which is located in the air exhaust duct from the separator, the external pressure source being the compressor of another turbomachine.