US 11,814,990 B2
Turbomachine turbine having a CMC nozzle with load spreading
Nicolas Paul Tableau, Moissy-Cramayel (FR); Sébastien Serge Francis Congratel, Moissy-Cramayel (FR); Antoine Claude Michel Etienne Danis, Moissy-Cramayel (FR); Matthieu Arnaud Gimat, Moissy-Cramayel (FR); and Gilles Gérard Claude Lepretre, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/755,288
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Oct. 28, 2020, PCT No. PCT/FR2020/051944
§ 371(c)(1), (2) Date Apr. 26, 2022,
PCT Pub. No. WO2021/084203, PCT Pub. Date May 6, 2021.
Claims priority of application No. 1912249 (FR), filed on Oct. 31, 2019.
Prior Publication US 2022/0364475 A1, Nov. 17, 2022
Int. Cl. F01D 9/04 (2006.01); F01D 5/28 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 5/282 (2013.01); F01D 9/042 (2013.01); F05D 2220/323 (2013.01); F05D 2240/128 (2013.01); F05D 2250/291 (2013.01); F05D 2250/38 (2013.01); F05D 2260/31 (2013.01); F05D 2260/36 (2013.01); F05D 2300/6033 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A turbomachine turbine comprising a casing, an outer metal support shroud integral with the casing, an inner metal support shroud, and an annular turbine distributor defining an axial direction and a radial direction and including a plurality of annular distributor sectors made of ceramic matrix composite material forming a crown extending between the outer support shroud and the inner support shroud,
each annular distributor sector including a metal mast, an inner platform, an outer platform and at least one blade extending radially between the inner and outer platforms and having a hollow profile that defines an inner housing extending radially, the inner and outer platforms each having an opening communicating with said inner housing of the blade, and the mast passing through said openings and the inner housing and being secured to said casing on the one hand and connected to said annular distributor sector on the other hand,
wherein each blade comprises at least one first radial shoulder projecting in the axial direction from an inner surface of the blade towards the inside of the blade, and each mast comprises at least one second shoulder projecting in the axial direction from an outer surface of the mast towards the outside of the mast configured to cooperate with said at least one first shoulder in the radial direction and radially press the blade against the mast, at least one first shoulder comprising a first beveled portion forming a first non-zero angle with the axial direction and at least one second shoulder comprising a second beveled portion forming a second non-zero angle with the axial direction, the first angle and the second angle having the same value.