US 11,988,385 B2
Production by additive manufacturing of complex parts
Jean-Paul Didier Autret, Moissy-Cramayel (FR); Thomas Sebastien Alexandre Gresy, Moissy-Cramayel (FR); Stéphane Lavignotte, Moissy-Cramayel (FR); and Nicolas Roland Guy Savary, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 18/002,011
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Jun. 9, 2021, PCT No. PCT/FR2021/051030
§ 371(c)(1), (2) Date Dec. 15, 2022,
PCT Pub. No. WO2021/255364, PCT Pub. Date Dec. 23, 2021.
Claims priority of application No. 2006204 (FR), filed on Jun. 15, 2020.
Prior Publication US 2023/0258337 A1, Aug. 17, 2023
Int. Cl. F23R 3/00 (2006.01); B33Y 80/00 (2015.01)
CPC F23R 3/002 (2013.01) [F23R 3/005 (2013.01); B33Y 80/00 (2014.12); F23R 2900/00018 (2013.01); F23R 2900/03042 (2013.01)] 4 Claims
OG exemplary drawing
 
1. A method of production by additive manufacturing of at least one part of an aeronautic turbomachine combustion chamber extending about an axis and comprising a radially outer wall which is lined locally by a radially inner wall so as to form therebetween an intermediate space that creates a film of air, wherein from bottom to top, and by additive manufacturing:
while, by depositing a succession of layers of material, a lower portion of said radially outer wall is created, the deposition of layers of said material is continued in order to erect, on said lower portion, bridges which are built up next to one another up to tops of said bridges, wherein:
the deposition of layers of said material is continued to create the radially inner wall, while continuing with erecting the radially outer wall, wherein the deposition of layers joins the radially inner wall and radially outer wall to the bridges; and
said deposition of layers of material is continued, at least until said lower portion of the radially outer wall and an end of the radially inner wall opposite to a location where the bridges join together, and:
by manufacturing, according to a polygonal design, around the axis, said radially external wall and radially internal wall, and
by manufacturing the bridges so that, between said radially outer wall and radially inner wall, the bridges extend in an inclined manner, not perpendicular to a side of a polygon where they are arranged,
so that the bridges are disposed adjacent to each other towards the end of the radially inner wall opposite to that where the radially inner wall joins the radially outer wall and wherein the radially inner wall is located in an upstream portion of the combustion chamber adjacent to an air fuel injection system for the combustion chamber.