Abstract: A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc and receives a ventilation air flow and of which the other is downstream of the disc, the upstream flange of the disc including a mechanism connecting to the upstream eternal cavity and the internal cavity for ventilating the hub of the disc.

Abstract: A diffuser which straightens the flow of air issuing from a centrifugal compressor in a turbine engine is provided. The diffuser having a cylindrical shape and including a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part, and a third part intended to open out into a downstream cavity, positioned downstream of the diffuser and fed with air issuing from the compressor. The first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the downstream cavity into communication with a bleed cavity situated upstream of the diffuser.

Abstract: A high pressure turbine of a turbomachine such as a turbojet, in which a control box of radial clearances of rotating blades are provided. An annular element including a determined flexibility has one end fixed to an annular support and the other end supported by a simple axial bearing with a given pressure on the upstream side of the control box. Thus, disturbing vibration loads are prevented at the attachment points of the control box with the external casing of turbines, thereby also eliminating the risk of cracks occurring.

Abstract: Diffuser intended to straighten the flow of air issuing from a centrifugal compressor in a turbine engine, the said diffuser having a cylindrical shape and comprising a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part and a third part intended to open out into a downstream cavity, positioned downstream of the said diffuser and fed with air issuing from the said compressor, characterized in that the first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the said downstream cavity into communication with a bleed cavity situated upstream of the said diffuser.

Abstract: A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc and receives a ventilation air flow and of which the other is downstream of the disc, the upstream flange of the disc including a mechanism connecting to the upstream eternal cavity and the internal cavity for ventilating the hub of the disc.