US 12,281,578 B2
Turbine shroud assembly
Clément Jarrossay, Moissy-Cramayel (FR); Sébastien Serge Francis Congratel, Moissy-Cramayel (FR); Antoine Claude Michel Etienne Danis, Moissy-Cramayel (FR); Aurélien Gaillard, Moissy-Cramayel (FR); and Nicolas Paul Tableau, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/913,310
Filed by Safran Aircraft Engines, Paris (FR)
PCT Filed Mar. 22, 2021, PCT No. PCT/FR2021/050469
§ 371(c)(1), (2) Date Sep. 21, 2022,
PCT Pub. No. WO2021/191538, PCT Pub. Date Sep. 30, 2021.
Claims priority of application No. 2002849 (FR), filed on Mar. 24, 2020.
Prior Publication US 2023/0116425 A1, Apr. 13, 2023
Int. Cl. F01D 11/08 (2006.01); F01D 11/24 (2006.01); F01D 25/24 (2006.01)
CPC F01D 11/24 (2013.01) [F01D 25/243 (2013.01); F05D 2220/32 (2013.01); F05D 2230/60 (2013.01); F05D 2240/11 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A turbine ring assembly comprising a plurality of ring sectors made of ceramic-matrix composite material forming a turbine ring and a ring support structure, each of said ring sector having, along a cutting plane defined by an axial direction and a radial direction of said turbine ring, said axial direction corresponding to the direction of flow of a gas stream in said turbine ring assembly, a base with, in said radial direction of said turbine ring, a radially inner face defining the inner face of said turbine ring and a radially outer face from which a first upstream attachment lug and a second downstream attachment lug protrude, said ring support structure including a shroud which extends around said turbine ring, from which an upstream radial clamp and a downstream radial clamp by which said first upstream and second downstream attachment lugs of each ring sector are held protrude radially towards the turbine ring, said shroud including, relative to said direction of flow of a gas stream in said turbine ring assembly:
a first upstream portion which extends radially above said first upstream attachment lug and a second downstream portion which extends in the extension of said first upstream portion and radially above said second downstream attachment lug, said first upstream portion having the shape of a right cylinder and said second downstream portion being frustoconical and, from one end of said first upstream portion, extending towards an axis of the turbine ring while having a generally constant thickness, wherein said first upstream portion and said second downstream portion form an angle comprised between 30° and 80°;
said upstream radial clamp extending from said upstream portion to bear, directly or indirectly, against said first upstream attachment lug, while said downstream radial clamp extends from said downstream portion to come into contact against said second downstream attachment lug, wherein said downstream radial clamp extends in a region of the second downstream portion farthest from the first upstream portion, wherein said turbine ring is held, relative to said upstream and downstream radial clamps, by axial pins which cooperate respectively on the one hand with said upstream radial clamp, via first and second annular flanges and directly with said downstream radial clamp, and on the other hand, with said first upstream and second downstream attachment lugs.