US 11,808,179 B2
Turbomachine hollow blade
Laurence Vial, Moissy-Cramayel (FR); Bruno Frelon, Moissy-Cramayel (FR); Jérôme Beugniez, Moissy-Cramayel (FR); and Yann Bellot, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/909,143
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Mar. 8, 2021, PCT No. PCT/FR2021/050390
§ 371(c)(1), (2) Date Sep. 2, 2022,
PCT Pub. No. WO2021/181038, PCT Pub. Date Sep. 16, 2021.
Claims priority of application No. 2002509 (FR), filed on Mar. 13, 2020.
Prior Publication US 2023/0144182 A1, May 11, 2023
Int. Cl. F01D 9/06 (2006.01); F01D 5/18 (2006.01); B33Y 80/00 (2015.01)
CPC F01D 9/065 (2013.01) [F01D 5/187 (2013.01); B33Y 80/00 (2014.12); F05D 2250/221 (2013.01); F05D 2250/28 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A turbomachine hollow vane, comprising at least one blade having lateral walls which are intended to guide a flow in a duct around the vane and which are attached on a first platform at a first longitudinal end of the at least one blade,
the at least one blade further comprising:
an internal cavity between the lateral walls, the internal cavity is intended for passing a cooling fluid of the at least one blade,
an opening for an inlet of the cooling fluid opening through said first platform,
characterised in that a gyroid surface array fills at least one portion of the internal cavity and is arranged to guide the cooling fluid into the internal cavity, and the gyroid surface array is in contact with at least one portion of the lateral walls.