US 12,031,455 B2
Turbomachine turbine having CMC nozzle with load spreading
Aurélien Gaillard, Moissy-Cramayel (FR); Antoine Claude Michel Etienne Danis, Moissy-Cramayel (FR); Clément Jarrossay, Moissy-Cramayel (FR); Gilles Gérard Claude Lepretre, Moissy-Cramayel (FR); and Nicolas Paul Tableau, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/617,565
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jun. 1, 2020, PCT No. PCT/FR2020/050928
§ 371(c)(1), (2) Date Dec. 8, 2021,
PCT Pub. No. WO2020/249886, PCT Pub. Date Dec. 17, 2020.
Claims priority of application No. 1906244 (FR), filed on Jun. 12, 2019.
Prior Publication US 2022/0228498 A1, Jul. 21, 2022
Int. Cl. F01D 9/04 (2006.01); F01D 5/18 (2006.01)
CPC F01D 9/04 (2013.01) [F01D 5/18 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01); F05D 2240/30 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A turbomachine turbine comprising a casing, an annular nozzle defining an axial direction and a radial direction, an outer support shroud of metal integral with the casing and an inner support shroud of metal, the nozzle comprising a plurality of nozzle sectors of ceramic matrix composite material forming a ring extending between the outer support shroud and the inner support shroud,
each sector including a mast, an inner platform, an outer platform and at least one airfoil extending radially between the inner and outer platforms and having a hollow profile defining an inner recess extending radially, the inner and outer platforms each having an opening communicating with said inner recess of the airfoil,
wherein the metal outer shroud comprises an opening for each mast, and for each sector the mast passes through said openings of the inner and outer platforms, said inner recess and one of the openings of the metal outer shroud, and the mast comprises at least one fastening projection to the outer support shroud having at least one portion extending from a radially outer end of the mast in a direction opposite to the center of the mast and in a plane orthogonal to the radial direction, said at least one fastening projection cooperating with a radially outer face of the outer support shroud,
wherein the mast comprises at least one protruding portion extending in a plane transverse to the radial direction, and the at least one protruding portion forms a support at a radial position of the mast, in the inner recess of the airfoil, and is in contact with the inner recess of the airfoil, wherein the at least one protruding portion is disposed only on an axial upstream-facing surface of the mast.