Abstract: A turbine rotor for a gas turbine engine, includes an upstream turbine disk; a downstream turbine disk; an annular flange; a first ferrule connecting the upstream turbine disk to the annular flange; a second ferrule connecting the downstream turbine disk to the annular flange; an air flow separator device including: a first part, forming a first ring, arranged between the upstream turbine disk and the downstream turbine disk; a second part, forming a second ring, having a first portion facing the downstream turbine disk, and a second portion arranged between the first ferrule and the second ferrule; and a thermal insulation area arranged between the first part and the second part.

Abstract: An impeller for a turbine engine is disclosed, such as a turbojet engine or a turboprop engine of an aircraft, for rotating about an axis of rotation in a predetermined direction of rotation and for having a flow of gas passing therethrough, comprising a series of blades distributed circumferentially about the axis of rotation of the wheel, the radially external end of each blade comprising a heel supporting at least one radially external lip, extending circumferentially in an oblique direction relative to the radial plane perpendicular to the axis of rotation, the lip being angled circumferentially in the downstream direction in the aforementioned direction of rotation such as to enable a compression of the gases located upstream from the lip during the rotation of the impeller.

Abstract: A turbine rotor for a gas turbine engine, includes an upstream turbine disk; a downstream turbine disk; an annular flange; a first ferrule connecting the upstream turbine disk to the annular flange; a second ferrule connecting the downstream turbine disk to the annular flange; an air flow separator device including: a first part, forming a first ring, arranged between the upstream turbine disk and the downstream turbine disk; a second part, forming a second ring, having a first portion facing the downstream turbine disk, and a second portion arranged between the first ferrule and the second ferrule; and a thermal insulation area arranged between the first part and the second part.

Abstract: A turbine wheel including a plurality of blades having roots engaged axially and held radially in slots in a disk alternating between teeth of the disk, in which the blades have platforms arranged circumferentially end to end and each connected to a blade root by a tang, is provided. Separator walls extend from the tangs in a circumferential direction and from upstream to downstream so as to define radially between the platforms and the teeth of the disk at least a radially inner cavity and a radially outer cavity between two adjacent tangs.

Abstract: The invention relates to an impeller for a turbine engine, such as a turbojet engine or a turboprop engine of an aircraft, intended for rotating about an axis of rotation in a predetermined direction of rotation (R) and for having a flow of gas passing therethrough, comprising a series of blades (7) distributed circumferentially about the axis of rotation of the wheel, the radially external end of each blade (7) comprising a heel (11) supporting at least one radially external lip (12, 13), extending circumferentially in an oblique direction (?1, ?2) relative to the radial plane (P) perpendicular to the axis of rotation, the lip (12, 13) being angled circumferentially in the downstream direction in the aforementioned direction of rotation (R) such as to enable a compression of the gases located upstream from the lip (12, 13) during the rotation of the impeller (1).

Abstract: The invention relates to a turbine wheel (104) comprising a plurality of blades having roots engaged axially and held radially in slots (34) in a disk (22) alternating between teeth (36) of the disk (22), the blades having platforms (100) arranged circumferentially end to end and each connected to a blade root (26) by a tang (102). According to the invention, separator walls (90) extend from the tangs (102) in a circumferential direction and from upstream to downstream so as to define radially between the platforms (100) and the teeth (36) of the disk at least a radially inner cavity (92) and a radially outer cavity (94) between two adjacent tangs.