SEALING RING FOR Aircraft TURBINE STEEL TURBINE STEPS CONTAINING CUTTING PINS WITH CUTS

摘要

1. An O-ring (60) designed to press against the rotor disk (20) of the turbine stage (10) for an aircraft turbomachine, containing a plurality of locking pins (66) that prevent the rotation of said ring relative to the rotor disk, with each pin (66 ) protrudes axially from the annular body (63) and has two opposite circular end surfaces (72) intended for placement and facing two directly following blades made on the rotor disk, characterized in that the axial split slot (70 ) passes radially through at least one of the said locking pins (66). 2. The ring according to claim 1, characterized in that each of the two opposite circular end surfaces (72) is connected to the bearing surface of the pins (68) provided on the annular body (63) by the first connecting radius (82), each of the two side faces (78) of the slot is connected at the base (74) of this slot by a second connecting radius (80), the second connecting radius (80) being substantially larger than the first connecting radius (82). 3. The ring according to claim 1, characterized in that the base (74) of the slot (70) of each pin (66) is located in the axial direction at the same level or near the base of the said pin. A ring according to claim 1, characterized in that the ratio between the width (I) of the slot (70) and the total width (L) of said locking pin (66), in the circumferential direction (92), is between 0.3 and 0.4. A ring according to claim 1, characterized in that the slot (70) is centered on said locking pin (66). The ring according to claim 1, characterized in that it has three locking pins (66) located at an angle