US 12,305,536 B2
Bladed turbine stator for a turbine engine
Jean Cahen, Moissy-Cramayel (FR); Cyril Leo Benoit, Moissy-Cramayel (FR); Jean-Philippe Mallat-Desmortiers, Moissy-Cramayel (FR); Romain Noselli, Moissy-Cramayel (FR); and Mireya Sanchez Gomez, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/000,065
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed May 26, 2021, PCT No. PCT/FR2021/050957
§ 371(c)(1), (2) Date Nov. 28, 2022,
PCT Pub. No. WO2021/245339, PCT Pub. Date Dec. 9, 2021.
Claims priority of application No. 2005835 (FR), filed on Jun. 4, 2020.
Prior Publication US 2023/0203959 A1, Jun. 29, 2023
Int. Cl. F01D 9/04 (2006.01); F01D 25/00 (2006.01); F01D 5/28 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 25/005 (2013.01); F01D 5/28 (2013.01); F05D 2220/32 (2013.01); F05D 2230/31 (2013.01); F05D 2240/12 (2013.01); F05D 2300/17 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A bladed turbine stator for a turbine engine, comprising two annular walls extending about a same axis, the walls being connected to each other by blades having an aerodynamic profile, the bladed turbine stator being divided into sectors and comprising several bladed stator sectors arranged circumferentially end to end about said axis, wherein the blades comprise first blades made of a first metal alloy, and second blades made of a second metal alloy different from the first alloy, each bladed stator sector comprising first blades and second blades, wherein the sectors are unitary one-piece elements separate from each other,
wherein each bladed stator sector comprises first blades at the circumferential ends of that sector, and second blades between those first blades and wherein the first alloy has:
a higher yield strength at 0.2% than the second alloy, or
a lower Young's modulus than the second alloy, or
a higher coefficient of expansion than the second alloy, or
a higher elongation at break than the second alloy.