US 12,031,447 B2
Method for manufacturing a turbine engine vane and turbine engine vane
Philippe Gabriel Louis Belaygue, Moissy-Cramayel (FR); Baptiste Romain Larrouy, Moissy-Cramayel (FR); and Olivier Philippe David Berteaux, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/757,936
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Dec. 15, 2020, PCT No. PCT/FR2020/052459
§ 371(c)(1), (2) Date Jul. 27, 2022,
PCT Pub. No. WO2021/130433, PCT Pub. Date Jul. 1, 2021.
Claims priority of application No. 19 15444 (FR), filed on Dec. 23, 2019.
Prior Publication US 2023/0018317 A1, Jan. 19, 2023
Int. Cl. F01D 25/00 (2006.01); B22D 27/04 (2006.01); B22F 10/28 (2021.01); B22F 10/66 (2021.01); B33Y 10/00 (2015.01); B33Y 40/20 (2020.01); B33Y 80/00 (2015.01); C30B 29/52 (2006.01); F01D 9/02 (2006.01)
CPC F01D 25/005 (2013.01) [B22D 27/045 (2013.01); B22F 10/28 (2021.01); B22F 10/66 (2021.01); B33Y 10/00 (2014.12); B33Y 40/20 (2020.01); B33Y 80/00 (2014.12); C30B 29/52 (2013.01); F01D 9/02 (2013.01); B22F 2301/15 (2013.01); F05D 2220/32 (2013.01); F05D 2230/20 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A method for manufacturing a blade comprising a first portion and a second portion, the method comprising:
forming the first portion, comprising
forming a model of the first portion from removable material,
forming a first shell mould from the model of the first portion, and
forming a single-crystal or columnar first portion from a first metal alloy in the first shell mould from a grain selector; and
forming the second portion in which the second portion is formed on the first portion, wherein the first portion and the second portion are made from different materials, the second portion being polycrystalline and formed from a second metal alloy.