US 11,867,091 B2
Turbine nozzle having blading made of ceramic matrix composite through which a metal ventilation circuit passes
Clément Jarrossay, Moissy-Cramayel (FR); Sébastien Serge Francis Congratel, Moissy-Cramayel (FR); Aurélien Gaillard, Moissy-Cramayel (FR); David René Pierre Le Cair, Moissy-Cramayel (FR); and Matthieu Arnaud Gimat, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN CERAMICS, Le Haillan (FR)
Appl. No. 17/766,711
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN CERAMICS, Le Haillan (FR)
PCT Filed Oct. 1, 2020, PCT No. PCT/FR2020/051722
§ 371(c)(1), (2) Date Apr. 5, 2022,
PCT Pub. No. WO2021/069816, PCT Pub. Date Apr. 15, 2021.
Claims priority of application No. 1911098 (FR), filed on Oct. 7, 2019.
Prior Publication US 2023/0313695 A1, Oct. 5, 2023
Int. Cl. F01D 9/04 (2006.01); F01D 9/06 (2006.01); F01D 11/00 (2006.01)
CPC F01D 9/042 (2013.01) [F01D 9/041 (2013.01); F01D 9/065 (2013.01); F01D 11/003 (2013.01); F05D 2240/128 (2013.01); F05D 2240/55 (2013.01); F05D 2300/6033 (2013.01); F05D 2300/614 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A nozzle for turbine of a turbine engine extending about a longitudinal central axis, said nozzle comprising a radially outer ring shell made of metallic material extending about said longitudinal central axis, a radially inner ring shell made of metallic material concentric with the radially outer ring shell, and a plurality of vanes made of ceramic matrix composite material in succession circumferentially about the longitudinal central axis, each vane extending radially between the radially inner ring shell and the radially outer ring shell, each vane having a hollow profile forming an inner recess opening at a radially inner end and at a radially outer end of said vane, wherein said nozzle comprises at least one liner made of metallic material forming a radial channel for conveying ventilation air passing through the inner recess of respectively one of the vanes, said liner comprising a radially outer end attached to the radially outer ring shell and a radially inner end which engages with the radially inner ring shell such that the radial channel is facing a respective opening of the radially inner ring shell to convey the ventilation air through said opening, the nozzle comprising at least one seal disposed between the radially inner ring shell and the liner so as to ensure the tightness between the radial channel and said opening of the radially inner ring shell, the liner comprising a shoulder forming a support surface radially facing a corresponding support surface of the radially inner ring shell such that the seal can be compressed radially between said support surfaces.