US 11,788,424 B2
Sealing ring for a wheel of a turbomachine turbine
Thomas Louis Guedot, Moissy-Cramayel (FR); Fabien Hourquet, Moissy-Cramayel (FR); Eloi Duflos, Moissy-Cramayel (FR); and Patrice Postel, Artiqueloutan (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/595,755
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed May 20, 2020, PCT No. PCT/FR2020/050841
§ 371(c)(1), (2) Date Nov. 23, 2021,
PCT Pub. No. WO2020/240118, PCT Pub. Date Dec. 3, 2020.
Claims priority of application No. 1905758 (FR), filed on May 29, 2019.
Prior Publication US 2022/0213800 A1, Jul. 7, 2022
Int. Cl. F01D 11/12 (2006.01); F01D 11/08 (2006.01); F01D 11/14 (2006.01); F02C 7/28 (2006.01)
CPC F01D 11/12 (2013.01) [F01D 11/08 (2013.01); F01D 11/14 (2013.01); F02C 7/28 (2013.01); F05D 2220/323 (2013.01); F05D 2230/31 (2013.01); F05D 2240/55 (2013.01)] 9 Claims
OG exemplary drawing
 
1. A sealing ring for a wheel of an aircraft turbomachine turbine, this ring comprising an annular body extending around an axis of revolution and comprising an outer surface and an inner surface which is coated with an annular layer of an abradable material, the ring further comprising an annular wall extending around the annular body and at a radial distance from this body, this annular wall comprising openings for passage of air for impact cooling on said outer surface, wherein the body and the wall are integrally formed, and
wherein the body and the wall define between them an annular space which is closed at a downstream end and open at an upstream end by reference to the flow of gases through the ring in operation.