Abstract: The invention relates to a turbine engine vane including a blade extending along a radial axis and a first cooling circuit arranged inside the blade, the first cooling circuit including a first cavity and a second cavity disposed downstream of the first cavity in a direction of circulation of a coolant in the blade, the first and second cavities radially extending inside the blade and being at least partly separated by a first radial partition having a radially internal free end, which at least partly demarcates a first coolant passage connecting the first and second cavities. According to the invention, the radially internal free end is enlarged by having a general transverse section substantially in the form of a keyhole.

Abstract: The invention relates to a turbine engine vane including a blade extending along a radial axis and a first cooling circuit arranged inside the blade, the first cooling circuit including a first cavity and a second cavity disposed downstream of the first cavity in a direction of circulation of a coolant in the blade, the first and second cavities radially extending inside the blade and being at least partly separated by a first radial partition having a radially internal free end, which at least partly demarcates a first coolant passage connecting the first and second cavities. According to the invention, the radially internal free end is enlarged by having a general transverse section substantially in the form of a keyhole.

Abstract: The invention relates to a turbine rotor, of a low-pressure turbine of a turbine engine for example, including a first disk, an annular seal ring including a radial flange on which is formed a scalloping defined by a plurality of scallops offering a locally increased surface, circularly distributed, said radial flange being attached to the rotor between the first disk and the second disk and a flow circuit including at least one lunule, suitable to place into fluid communication a radially inner cavity and a radially outer cavity, the lunule being formed on the radial flange of the seal ring said lunule being provided on at least one scallop.

Abstract: The invention relates to a turbine rotor, of a low-pressure turbine of a turbine engine for example, comprising: a first disk, a second disk, an annular seal ring comprising a radial flange on which is formed a scalloping defined by a plurality of scallops offering a locally increased surface, circularly distributed, said radial flange being attached to the rotor between the first disk and the second disk, and a flow circuit including at least one lunule, suitable to place into fluid communication a radially inner cavity and a radially outer cavity, the lunule being formed on the radial flange of the seal ring, said lunule being provided on at least one scallop.