US 12,123,320 B2
Turbomachine stator assembly comprising an inner shroud having upstream and downstream portions assembled by axial translation
Aurelien Gaillard, Moissy-Cramayel (FR); Sebastien Serge Francis Congratel, Moissy-Cramayel (FR); Clement Jarrossay, Moissy-Cramayel (FR); Pascal Cedric Tabarin, Moissy-Cramayel (FR); and Nicolas Paul Tableau, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/758,893
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jan. 14, 2021, PCT No. PCT/FR2021/050063
§ 371(c)(1), (2) Date Jul. 15, 2022,
PCT Pub. No. WO2021/148739, PCT Pub. Date Jul. 29, 2021.
Claims priority of application No. 2000640 (FR), filed on Jan. 23, 2020.
Prior Publication US 2023/0051167 A1, Feb. 16, 2023
Int. Cl. F01D 5/22 (2006.01); F01D 11/00 (2006.01); F01D 25/28 (2006.01)
CPC F01D 5/225 (2013.01) [F01D 11/006 (2013.01); F01D 25/28 (2013.01); F05D 2240/11 (2013.01); F05D 2240/80 (2013.01); F05D 2260/31 (2013.01); F05D 2300/6033 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A stator assembly for a turbomachine having a central longitudinal axis and comprising:
an outer shroud extending around said central longitudinal axis,
an inner shroud concentric with the outer shroud, and
a blade extending radially between the inner shroud and the outer shroud, the blade being connected to the inner shroud via a first connecting means, the blade delimiting a channel configured to convey ventilation air from a cavity extending radially outside the outer shroud to a cavity extending radially inside the inner shroud,
wherein the inner shroud comprises an upstream portion and a downstream portion forming two parts separate from each other and extending respectively from an axially upstream side and from an axially downstream side of said first connecting means when said parts are in an assembled configuration, the upstream portion being configured to be placed, when assembling the inner shroud, in the assembled configuration by axial translation of said upstream portion relative to the blade in a first direction extending from said upstream side to said downstream side, the downstream portion being configured to be placed, when assembling the inner shroud, in the assembled configuration by axial translation of said downstream portion relative to the blade in a second direction extending from said downstream side to said upstream side,
wherein the assembly further comprises second connecting means connecting the upstream portion and the downstream portion of the inner shroud to each other so as to maintain the upstream portion and the downstream portion in said assembled configuration,
wherein both the upstream portion and the downstream portion delimit a main flow path for circulation of gases, and
wherein the assembly further comprises a first sealing member integral with an upstream end of a radially inner platform of the blade and a second sealing member integral with a downstream end of the radially inner platform of the blade, the upstream portion of the inner shroud comprising a sealing face axially bearing on the first sealing member, the downstream portion of the inner shroud comprising a sealing face axially bearing on the second sealing member.