US 11,795,838 B2
Aircraft turbine shroud cooling device
Clément Jarrossay, Moissy-Cramayel (FR); Antoine Claude Michel Etienne Danis, Moissy-Cramayel (FR); Lucien Henri Jacques Quennehen, Moissy-Cramayel (FR); Nicolas Paul Tableau, Moissy-Cramayel (FR); and Sébastien Serge Francis Congratel, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/597,320
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jun. 25, 2020, PCT No. PCT/FR2020/051108
§ 371(c)(1), (2) Date Jan. 3, 2022,
PCT Pub. No. WO2021/001615, PCT Pub. Date Jan. 7, 2021.
Claims priority of application No. 1907464 (FR), filed on Jul. 4, 2019.
Prior Publication US 2022/0316357 A1, Oct. 6, 2022
Int. Cl. F01D 25/14 (2006.01); F01D 25/12 (2006.01); F01D 25/32 (2006.01)
CPC F01D 25/14 (2013.01) [F01D 25/12 (2013.01); F01D 25/32 (2013.01); F05D 2240/12 (2013.01); F05D 2260/20 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A device for cooling a turbine shroud comprising:
at least one annular flange configured to be attached to an annular radial collar of a shroud support structure being arranged upstream of the turbine shroud and comprising at least one cooling air circulation channel,
a diffuser configured to be attached to said annular radial collar downstream of the annular flange and comprising at least one intake channel in fluid communication with the circulation channel of the annular flange, and comprising an injection cavity comprising a plurality of injection holes and being configured to inject cooling air originating in the intake channel on a radially external face of the shroud, via the injection holes,
a particle filter arranged on an inlet section of the circulation channel of the annular flange, the particle filter comprising a plurality of openings, the diameter of these openings being less than the diameter of the injection holes of the diffuser, the at least one annular flange, the diffuser and the shroud support structure being separate structures.