US 11,946,387 B2
Turbine engine blade with improved cooling
Erwan Daniel Botrel, Moissy-Cramayel (FR); Kevin Yannick Garles, Moissy-Cramayel (FR); and Laurent Patrick Robert Coudert, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/617,981
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jun. 11, 2020, PCT No. PCT/FR2020/050995
§ 371(c)(1), (2) Date Dec. 10, 2021,
PCT Pub. No. WO2020/249905, PCT Pub. Date Dec. 17, 2020.
Claims priority of application No. 1906284 (FR), filed on Jun. 13, 2019.
Prior Publication US 2022/0316345 A1, Oct. 6, 2022
Int. Cl. F01D 5/18 (2006.01); F01D 5/30 (2006.01)
CPC F01D 5/187 (2013.01) [F01D 5/30 (2013.01); F05D 2220/323 (2013.01); F05D 2300/603 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A turbine vane of a turbomachine, comprising:
a root carrying a blade extending along a span direction, said blade comprising a trailing edge provided with cooling vents, a first serpentine circuit, and a second serpentine circuit, wherein:
each serpentine circuit includes several ducts extending along the span direction by being connected to each other through bent portions;
each serpentine circuit is supplied with air by a mouth located at the root via its duct which is furthest from the trailing edge;
the first serpentine circuit has an even number of ducts and the second serpentine circuit has an odd number of ducts, or vice versa,
the first serpentine circuit and the second serpentine circuit are terminated by a first terminal duct and a second terminal duct respectively, the first and second terminal ducts running along the trailing edge as an extension of each other, and by being separated from each other by an inner partition wall of the blade, and
the vents are supplied with cooling air from the first serpentine circuit and from the second serpentine circuit.