US 11,808,172 B2
Turbine engine vane equipped with a cooling circuit and lost-wax method for manufacturing such a vane
Romaine Pierre Cariou, Moissy-Cramayel (FR); Vianney Simon, Moissy-Cramayel (FR); Myriam Pelleterat De Borde, Moissy-Cramayel (FR); and Adrien Bernard Vincent Rollinger, Moissy-Cramayel (FR)
Assigned to Safran, Paris (FR); and Safran Aircraft Engines, Paris (FR)
Appl. No. 17/439,580
Filed by SAFRAN, Paris (FR); and SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Mar. 16, 2020, PCT No. PCT/FR2020/050564
§ 371(c)(1), (2) Date Sep. 15, 2021,
PCT Pub. No. WO2020/193912, PCT Pub. Date Oct. 1, 2020.
Claims priority of application No. 1903019 (FR), filed on Mar. 22, 2019.
Prior Publication US 2022/0154584 A1, May 19, 2022
Int. Cl. B22D 25/02 (2006.01); B22C 7/02 (2006.01); F01D 9/02 (2006.01)
CPC F01D 9/02 (2013.01) [B22C 7/02 (2013.01); B22D 25/02 (2013.01); F05D 2230/21 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A metal casting assembly for the manufacture of a turbine engine vane comprising a blade extending along a radial axis and a first cooling circuit arranged inside the blade, the first cooling circuit comprising a first cavity and a second cavity disposed downstream of the first cavity in a direction of circulation of a coolant in the blade, the first cavity and the second cavity being at least partly separated by a first radial partition having a radially internal free end which at least partly demarcates a first coolant passage connecting the first and second cavities, the assembly comprising a first core elongated along a radial height and which comprises a first wing intended to form the first cavity and a second wing intended to form the second cavity, the first wing and second wings being spaced apart along first space which is substantially constant along a majority of their radial height and being connected at one of their first ends, the first space being intended to form the first radial partition which separates the first and second cavities of the blade, the first space being enlarged at the first ends of the first wing and second wings, by having a transverse section substantially in the form of a keyhole, wherein the assembly comprises a second core elongated along the radial height and an elongated connecting element which is at least partly accommodated in the first space enlarged in a transverse direction perpendicular to the radial height and configured to hold the second core in position with respect to the first core.
 
9. A lost wax method for manufacturing a turbine engine vane, wherein the method comprises the following steps:
assembling a first core and a second core of a metal casting assembly with respect to each other with at least one connecting element which is elongated and inserted in an enlarged space in the form of a keyhole in a direction transverse to a radial height of a first wing and a second wing, the second core abutting against the at least one connecting element,
injecting wax so as to encapsulate the first and second cores assembled with the at least one connecting element and form a pattern,
manufacturing a shell enveloping the pattern,
pouring molten metal into the shell so as to form the turbine engine vane, and
shaking out the shell and the first and second cores so as to release the turbine engine vane and form first and second cavities of a first cooling circuit in a blade.