US 11,994,032 B2
Abradable member for a turbine of a turbomachine, comprising a wear face provided with guide vanes
Julian Nicolas Girardeau, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/632,475
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jul. 31, 2020, PCT No. PCT/FR2020/051419
§ 371(c)(1), (2) Date Feb. 2, 2022,
PCT Pub. No. WO2021/023936, PCT Pub. Date Feb. 11, 2021.
Claims priority of application No. 1909026 (FR), filed on Aug. 6, 2019.
Prior Publication US 2022/0275731 A1, Sep. 1, 2022
Int. Cl. F01D 11/12 (2006.01); B33Y 80/00 (2015.01)
CPC F01D 11/122 (2013.01) [B33Y 80/00 (2014.12); F05D 2240/129 (2013.01); F05D 2240/55 (2013.01); F05D 2250/283 (2013.01)] 9 Claims
OG exemplary drawing
 
1. An abradable member for a turbomachine turbine, comprising:
a cellular structure comprising walls defining wells which open through a wear face,
wherein the cellular structure comprises at least one flow straightener jutting from the wear face,
wherein the at least one flow straightener has a curved wall fastened to a well, and
wherein the curved wall extends perpendicularly to the well and presents an entry angle and an exit angle with respect to a longitudinal direction of the turbomachine turbine, the entry angle being greater than the exit angle.