US 11,719,102 B2
Blade provided with a cooling circuit
Michel Slusarz, Moissy-Cramayel (FR); Patrice Eneau, Moissy-Cramayel (FR); and Charlotte Marie Dujol, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/629,482
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jul. 24, 2020, PCT No. PCT/FR2020/051367
§ 371(c)(1), (2) Date Jan. 24, 2022,
PCT Pub. No. WO2021/019170, PCT Pub. Date Feb. 4, 2021.
Claims priority of application No. 1908825 (FR), filed on Aug. 1, 2019.
Prior Publication US 2022/0268160 A1, Aug. 25, 2022
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/18 (2013.01) [F05D 2220/30 (2013.01); F05D 2240/30 (2013.01); F05D 2260/20 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A blade for a turbomachine extending longitudinally between a base and an apex, comprising a lower surface wall, an upper surface wall, a leading edge and a trailing edge and comprising a plurality of internal ventilation cavities which form a cooling circuit of the blade,
wherein several ventilation cavities are ventilation cavities of a first type comprising
at least one ascending portion which extends longitudinally between the base and the apex, engaged with the lower surface wall and spaced from the upper surface wall, and
at least one discharge portion which extends towards and which opens at the trailing edge via at least one port of the trailing edge, and
wherein at least one ventilation cavity of the first type further comprises at least one descending portion which extends longitudinally from the apex engaged with the upper surface wall and spaced from the lower surface wall.