	US 12,392,256 B2
	Superalloy turbomachine part with an optimized hafnium content
Joel Delautre, Moissy-Cramayel (FR); Christophe Philippe Audic, Moissy-Cramayel (FR); Sarah Hamadi, Moissy-Cramayel (FR); Virginie Jaquet, Moissy-Cramayel (FR); Fernando Pedraza Diaz, La Rochelle (FR); and Annie Pasquet, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR); SAFRAN, Paris (FR); CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, Paris (FR); and UNIVERSITE DE LA ROCHELLE, La Rochelle (FR)
Appl. No. 17/797,920
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR); SAFRAN, Paris (FR); CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, Paris (FR); and UNIVERSITE DE LA ROCHELLE, La Rochelle (FR)
PCT Filed Feb. 2, 2021, PCT No. PCT/FR2021/050187 § 371(c)(1), (2) Date Aug. 5, 2022, PCT Pub. No. WO2021/156564, PCT Pub. Date Aug. 12, 2021.
Claims priority of application No. 2001166 (FR), filed on Feb. 6, 2020.
Prior Publication US 2023/0076728 A1, Mar. 9, 2023
Int. Cl. F01D 25/00 (2006.01); C22C 19/05 (2006.01); F01D 9/04 (2006.01); F23R 3/00 (2006.01)

CPC F01D 25/005 (2013.01) [C22C 19/057 (2013.01); F01D 9/04 (2013.01); F23R 3/002 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2240/35 (2013.01); F05D 2300/175 (2013.01)]

9 Claims

1. A turbomachine part comprising a nickel-based superalloy substrate comprising, in mass content, 5.0% to 8.0% cobalt, 6.5% to 10% chromium, 0.5% to 2.5% molybdenum, 5.0% to 9.0% tungsten, 6.0% to 9.0% tantalum, 4.5% to 5.8% aluminum, hafnium in a mass content between 500 ppm and 1100 ppm, and optionally comprising niobium in a mass content less than or equal to 1.5%, and optionally at least one of carbon, zirconium and boron each in a mass content less than or equal to 100 ppm, the remainder being nickel and unavoidable impurities.