ROUND PART FOR GAS TURBINE ENGINE ROTOR, RELATED GAS TURBINE ENGINE ROTOR, GAS TURBINE ENGINE MODULE AND GAS TURBINE ENGINE

摘要

The invention relates to a rotationally symmetrical part, such as a disk (24′), for a turbine engine rotor. Said part has a rotational axis (A) and comprises, on the periphery thereof, an annular row of teeth (22′), said teeth defining grooves (34′, 34″) therebetween for therein holding fir tree-shaped rotor blade roots (10′, 10″). Each tooth comprises a first side flank (40″), comprising at least two projecting portions that are intended for holding a blade root and are separate from each other by a hollow portion, and a second side flank (40′) comprising at least two projecting portions (42) that are intended for holding an adjacent blade root and are separated from each other by a hollow portion. Said at least two projecting portions of the first flank are located on circumferences (C3, C7) centered on the rotational axis of the rotationally symmetrical part, and said at least two projecting portions of the second flank are located on circumferences (C4, C8) centered on said rotational axis. Said part is characterized in that each tooth has, on substantially the entire longitudinal dimension thereof, a lack of symmetry in relation to a substantially radial median longitudinal plane (P2). At least one (C4) of said circumferences of the projecting portions of the second flank of each tooth is located between the circumferences (C3, C7) of the projecting portions of the first flank and is radially shifted from said circumferences.