US 12,129,761 B2
Aircraft turbomachine casing and method of manufacturing same
Meredith Roberts, Moissy-Cramayel (FR); Chris Anderson, Moissy-Cramayel (FR); Nicolas François Paul Broussais-Colella, Moissy-Cramayel (FR); Ambroise Nicolas Marie Malfroy, Moissy-Cramayel (FR); Foster Alexander Maxwell, Moissy-Cramayel (FR); Paul Myslinski, Moissy-Cramayel (FR); and Adrienne Retiveau-Leca, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN AEROSPACE COMPOSITES, Rochester, NH (US)
Appl. No. 17/795,511
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN AEROSPACE COMPOSITES, Rochester, NH (US)
PCT Filed Jan. 26, 2021, PCT No. PCT/FR2021/050136
§ 371(c)(1), (2) Date Jul. 26, 2022,
PCT Pub. No. WO2021/152251, PCT Pub. Date Aug. 5, 2021.
Claims priority of application No. 2000866 (FR), filed on Jan. 29, 2020.
Prior Publication US 2023/0075984 A1, Mar. 9, 2023
Int. Cl. F01D 11/12 (2006.01); B05C 5/02 (2006.01); B05C 9/06 (2006.01); B05C 11/02 (2006.01); B05C 11/10 (2006.01); B05C 17/10 (2006.01); B05D 1/40 (2006.01); B05D 3/12 (2006.01); B05D 7/22 (2006.01)
CPC F01D 11/122 (2013.01) [B05C 5/0216 (2013.01); B05C 9/06 (2013.01); B05C 11/025 (2013.01); B05C 11/1036 (2013.01); B05C 17/10 (2013.01); B05D 1/40 (2013.01); B05D 3/12 (2013.01); B05D 7/22 (2013.01); F05D 2230/31 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A method for manufacturing an aircraft turbomachine casing, this casing comprising:
an annular envelope extending around an axis A and made of a composite material comprising fibers which are woven and embedded in a resin,
an annular layer of abradable material extending inside the envelope, and
support panels extending around the axis A and interposed between the envelope and the abradable layer,
wherein the method comprises the steps of:
a) preparing a paste by mixing at least two components,
b) depositing the paste on an internal annular surface of the panels,
c) spreading the paste by means of at least one roll extending parallel to the axis A and configured to roll on guide annulus arranged on either side of the panels or of the envelope, coaxially thereto, so as to form an angular sector of the abradable layer which extends over a predetermined angle about the axis A,
d) forming a chamfer at a circumferential end of the sector thus formed,
e) and repeating the steps a) to d) until a plurality of consecutive angular sectors of the abradable layer are formed and cover the entire internal surface of the panels, the sectors formed in the step e) each comprising a circumferential end covering the chamfered circumferential end of the previously deposited sector.