US 12,247,494 B2
Turbine engine assembly comprising a casing and an aerodynamic treatment member at the blade tips, and corresponding turbine engine
Gabriel Perez, Moissy-Cramayel (FR); Mickael Vincent Philit, Moissy-Cramayel (FR); and William Henri Joseph Riera, Moissy-Cramayel (FR)
Assigned to SAFRAN, Paris (FR)
Appl. No. 18/556,803
Filed by SAFRAN, Paris (FR)
PCT Filed Apr. 26, 2022, PCT No. PCT/FR2022/050793
§ 371(c)(1), (2) Date Oct. 23, 2023,
PCT Pub. No. WO2022/229555, PCT Pub. Date Nov. 3, 2022.
Claims priority of application No. 2104403 (FR), filed on Apr. 28, 2021.
Prior Publication US 2024/0200468 A1, Jun. 20, 2024
Int. Cl. F01D 25/24 (2006.01); F01D 9/04 (2006.01); F04D 19/00 (2006.01); F04D 29/52 (2006.01); F04D 29/68 (2006.01)
CPC F01D 25/24 (2013.01) [F01D 9/041 (2013.01); F04D 19/00 (2013.01); F04D 29/526 (2013.01); F04D 29/685 (2013.01); F05D 2240/11 (2013.01)] 13 Claims
OG exemplary drawing
 
1. An assembly comprising a casing for a turbine engine, the turbine engine casing comprising an annular or cylindrical radially outer shell provided with a radially inner surface, and an aerodynamic treatment member comprising a plurality of grooves distributed in a circumferential direction, wherein the radially outer shell comprises a circumferential recess in which the aerodynamic treatment member is removably mounted, the treatment member extending along at least one angular sector and being complementary in shape to the circumferential recess, the treatment member comprising a circumferential opening into which the plurality of grooves opens.