US 12,146,420 B2
Aircraft turbomachine blade and method for manufacturing same using lost-wax casting
Michel Slusarz, Moissy-Cramayel (FR); Pierre Guillaume Auzillon, Moissy-Cramayel (FR); Patrice Eneau, Moissy-Cramayel (FR); and Léandre Ostino, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/440,853
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Mar. 11, 2020, PCT No. PCT/FR2020/050496
§ 371(c)(1), (2) Date Sep. 20, 2021,
PCT Pub. No. WO2020/193899, PCT Pub. Date Oct. 1, 2020.
Claims priority of application No. 1903021 (FR), filed on Mar. 22, 2019.
Prior Publication US 2022/0170371 A1, Jun. 2, 2022
Int. Cl. F01D 5/18 (2006.01); F01D 5/14 (2006.01)
CPC F01D 5/147 (2013.01) [F01D 5/187 (2013.01); F05D 2220/32 (2013.01); F05D 2230/21 (2013.01)] 9 Claims
OG exemplary drawing
 
1. An aircraft turbine engine blade, comprising at least one inner cavity configured to circulate a ventilation air flow, the cavity comprising a wall that comprises first projecting elements oriented in at least one first direction and forming air flow disrupters, the wall further comprising at least one second projecting element oriented in at least one second direction different from the first direction, wherein the second projecting element and at least one of the first projecting elements overlap each other in an area, at least one of the first projecting elements overlapping the second projecting element and having a height greater than a height of the second projecting element in said area and which is greater than that of the other first projecting elements of the wall, to retain a disruptive function over an entire length thereof, and wherein only one of the first projecting elements overlaps said second projecting element and forms a cross with the second projecting element.