US 12,270,312 B2
Ventilation ring for the rear bearing support member of an aircraft turbine engine
Mickaël Voiron, Moissy-Cramayel (FR); Fabien Stéphane Garnier, Moissy-Cramayel (FR); and Nicolas Ovaere, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/273,138
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jan. 20, 2022, PCT No. PCT/FR2022/050109
§ 371(c)(1), (2) Date Jul. 19, 2023,
PCT Pub. No. WO2022/157456, PCT Pub. Date Jul. 28, 2022.
Claims priority of application No. 2100558 (FR), filed on Jan. 21, 2021.
Prior Publication US 2024/0125249 A1, Apr. 18, 2024
Int. Cl. F01D 25/16 (2006.01); F01D 25/12 (2006.01)
CPC F01D 25/125 (2013.01) [F01D 25/162 (2013.01); F05D 2230/23 (2013.01); F05D 2260/20 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A ventilation ring for a bearing support member of an aircraft turbine engine, the ventilation ring comprising:
at least two tubular walls extending opposite each other,
at least one of the at least two tubular walls comprising a main portion and a base,
the base having a thickness greater than a thickness of the main portion, and
at least one spacer wall connecting the tubular walls,
the at least one spacer wall having at least one aperture extending into the base,
the at least one spacer wall having a rim around the at least one aperture,
an entirety of the rim having a thickness greater than a thickness of the at least one spacer wall at a distance from the rim.