US 12,270,307 B2
Turbine rotor for a turbomachine
Julian Nicolas Girardeau, Moissy-Cramayel (FR); and Benoit Guillaume Silet, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/271,893
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jan. 18, 2022, PCT No. PCT/FR2022/050095
§ 371(c)(1), (2) Date Jul. 12, 2023,
PCT Pub. No. WO2022/157448, PCT Pub. Date Jul. 28, 2022.
Claims priority of application No. 2100570 (FR), filed on Jan. 21, 2021.
Prior Publication US 2024/0117750 A1, Apr. 11, 2024
Int. Cl. F01D 11/12 (2006.01); F01D 5/20 (2006.01); F01D 5/22 (2006.01)
CPC F01D 11/122 (2013.01) [F01D 5/20 (2013.01); F01D 5/225 (2013.01); F05D 2250/11 (2013.01); F05D 2250/12 (2013.01); F05D 2250/18 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A rotor of a turbine extending around a longitudinal axis,
the rotor comprising at least one rotor disc bearing at a periphery of the at least one rotor disc at least one blade, each blade comprising an airfoil a heel being provided at the radially outer end of the airfoil,
wherein the heel comprises a platform equipped with an upstream lip and a downstream lip which extend radially outward from the platform,
wherein the platform has a front lateral edge and a back lateral edge with respect to the direction of rotation of the rotor about the longitudinal axis, during the operation of the turbine,
wherein the airfoil has a suction face,
wherein the platform has a suction face portion which extends from the front lateral edge to the suction face of the airfoil,
wherein the upstream lip and the downstream lip each comprise sawtooth-shaped cut-outs forming a front tooth and a back tooth on each lip with respect to the direction of rotation of the rotor about the longitudinal axis,
wherein the front tooth and the back tooth of each lip are formed into a triangular shape or a truncated rectangle shape,
wherein the front tooth and the back tooth of each lip are contiguous,
wherein the front tooth of the upstream lip and the front tooth of the downstream lip have a front edge perpendicular to the platform and a radially outer edge which is straight and inclined backward from an apex of the front edge in the direction of the platform,
wherein the back tooth of the upstream lip and the back tooth of the downstream lip have a cutting edge perpendicular to the platform and a radially outer edge which is straight and inclined backward from an apex of the cutting edge in the direction of the platform, and
wherein the front tooth of each lip is disposed on the suction face portion of the platform,
wherein the cutting edge of the back tooth of the downstream lip is disposed nearer to the suction face of the airfoil than to the front lateral edge of the platform.