US 12,377,464 B2
Method for manufacturing a metal part
Hugo Sistach, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/630,739
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jul. 28, 2020, PCT No. PCT/FR2020/051391
§ 371(c)(1), (2) Date Jan. 27, 2022,
PCT Pub. No. WO2021/023925, PCT Pub. Date Feb. 11, 2021.
Claims priority of application No. 1909002 (FR), filed on Aug. 6, 2019.
Prior Publication US 2022/0258235 A1, Aug. 18, 2022
Int. Cl. B22F 7/06 (2006.01); B22F 3/22 (2006.01); B22F 5/04 (2006.01); B22F 10/28 (2021.01); B33Y 10/00 (2015.01); B33Y 80/00 (2015.01)
CPC B22F 7/06 (2013.01) [B22F 3/225 (2013.01); B22F 5/04 (2013.01); B22F 10/28 (2021.01); B33Y 10/00 (2014.12); B33Y 80/00 (2014.12)] 3 Claims
OG exemplary drawing
 
1. A method for manufacturing a metal part comprising:
forming by additive manufacturing, a blank of a first portion of the metal part to be manufactured, comprising a first binder and a first metal powder present in the first binder,
forming by injection molding, a blank of a second portion of the metal part to be manufactured, comprising a second binder and a second metal powder present in the second binder wherein the blank of the second portion is overmolded over the blank of the first portion during the injection molding,
debinding the blank of the first portion and the blank of the second portion, wherein the blank of the first portion and the blank of the second portion are separately debound to produce a first debound blank and a second debound blank, and
assembling the first debound blank and the second debound blank after the debinding, joint sintering of the first debound blank and of the second debound blank to obtain the metal part, the first and the second blanks being in contact during sintering,
a ratio between a volume content of powder in the first blank and a volume content of powder in the second blank being comprised between 0.6 and 1.6, wherein the metal part is an aeronautical turbomachine blade wherein the first portion comprises an internal portion of the aeronautical turbomachine blade including at least one cooling channel, and wherein the second portion comprises an aerodynamic profile of the aeronautical turbomachine blade.