Nickel-based alloy comprising tantalum

Patent metadata

Field	Value
Publication number	US-2025043393-A1
Application number	US-202218718733-A
Country	US
Kind code	A1
Filing date	Dec 14, 2022
Priority date	Dec 15, 2021
Publication date	Feb 6, 2025
Grant date	—

Abstract

The invention relates to a nickel-based alloy comprising, in weight percent: 4.0 to 20.0% cobalt, 14.0 to 18.5% chromium, 1.8 to 2.6% aluminum, 1.3 to 1.9% titanium, 5.5 to 6.5% tantalum, 0.01 to 0.10% carbon, 0.003 to 0.02% boron, and 0.01 to 0.10% zirconium. A method for manufacturing a part made of the nickel-based alloy includes preparing a billet which has the same composition as that of the nickel-based alloy, shaping the part, and heat treating the part.

First claim

1 . A nickel-based alloy comprising, in weight percent:
4.0 to 20.0% cobalt; 14.0 to 18.5% chromium; 1.8 to 2.6% aluminum; 1.3 to 1.9% titanium; 5.5 to 6.5% tantalum; 0.01 to 0.10% carbon; 0.003 to 0.02% boron; et 0.01 to 0.10% zirconium; 0 to 5.0% molybdenum; 0 to 5.0% iron; 0 to 9.0 tungsten; and 0 to 1.0% niobium.

2 . The nickel-based alloy according to claim 1 , comprising, in weight percent:
0.02 to 0.05% carbon.

3 . The nickel-based alloy according to claim 1 , comprising, in weight percent:
2.0 to 2.5% aluminum; 1.4 to 1.8% titanium; and 5.7 to 6.4% tantalum.

4 . A method for manufacturing a part made of a nickel-based alloy according to claim 1 , the method comprising:
manufacturing a billet which has the same composition as that of the nickel-based alloy; shaping the part; and heat treating the part.

5 . The method according to claim 4 , wherein heat treating the part comprises at least one treatment among:
a γ′ supersolvus solution heat treatment, preferably at a temperature that is 10 to 40° C. higher than the γ′ solvus; and a γ′ subsolvus solution heat treatment, preferably at a temperature that is 10 to 40° C. lower than the γ′ solvus.

6 . The method according to claim 4 , wherein the heat treatment further comprises:
a tempering to precipitate M 23 C 6 type carbides, preferably by heating to a temperature between 825 and 870° C.; and optionally a tempering to stabilize the populations of γ′ precipitates, preferably at a temperature between 76° and 825° C.

7 . An aeronautical part made of an alloy according to claim 1 , in particular a turbine casing.

8 . The nickel-based alloy according to claim 2 , comprising, in weight percent:
2.0 to 2.5% aluminum; 1.4 to 1.8% titanium; and 5.7 to 6.4% tantalum.

9 . A method for manufacturing a part made of a nickel-based alloy according to claim 2 , the method comprising:
manufacturing a billet which has the same composition as that of the nickel-based alloy; shaping the part; and heat treating the part.

10 . A method for manufacturing a part made of a nickel-based alloy according to claim 3 , the method comprising:
manufacturing a billet which has the same composition as that of the nickel-based alloy; shaping the part; and heat treating the part.

11 . The method according to claim 5 , wherein the heat treatment further comprises:
a tempering to precipitate M 23 C 6 type carbides, preferably by heating to a temperature between 825 and 870° C.; and optionally a tempering to stabilize the populations of γ′ precipitates, preferably at a temperature between 76° and 825° C.

12 . An aeronautical part made of an alloy according to claim 2 , in particular a turbine casing.

13 . An aeronautical part made of an alloy according to claim 3 , in particular a turbine casing.

Assignees

• Safran
• Aubert & Duval Sa

Inventors

• Rouffie Anne-Laure
• Franchet Jean-Michel Patrick Maurice
• Menou Edern
• Crozet Coraline
• Finet Laurane

Classifications

• C22F1/10

  of nickel or cobalt or alloys based thereon · CPC title

• C22C1/023

  Alloys based on nickel · CPC title

• C22C19/056 Primary

  with the maximum Cr content being at least 10% but less than 20% · CPC title

• C22C19/05 Primary

  with chromium · CPC title