Turbine component made from superalloy comprising rhenium and associated manufacturing process

Patent metadata

Field	Value
Publication number	US-11293290-B2
Application number	US-201816757184-A
Country	US
Kind code	B2
Filing date	Oct 17, 2018
Priority date	Oct 20, 2017
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

A turbine component includes a substrate made from monocrystalline nickel-based superalloy including rhenium, which has a γ-γ′ Ni phase, and an average weight faction of chromium of less than 0.08, a sublayer made from nickel-based metal superalloy covering the substrate, in which the sublayer made from metal superalloy includes at least aluminium, nickel, chromium, silicon, hafnium and has, predominantly by volume, a γ′-Ni 3 Al phase.

First claim

The invention claimed is:

1. A turbine component comprising:
a substrate of single-crystal nickel-based superalloy, comprising rhenium, having a γ-γ′ Ni phase, and an average chromium mass fraction of less than 0.08; and
a nickel-based metal superalloy sublayer covering the substrate,
wherein:
the metal superalloy sublayer comprises at least aluminum, nickel, chromium, silicon, and hafnium and has a γ′-Ni3Al phase predominantly by volume, and
the turbine component further comprises an aluminum oxide protective layer covering the sublayer.

2. The component of claim 1 , wherein the sublayer also has a γ-Ni phase.

3. The component of claim 1 , wherein the average rhenium mass fraction of the substrate is greater than 0.04.

4. The component of claim 1 , wherein an average platinum mass fraction of the sublayer is less than 0.05.

5. The component of claim 1 , wherein the average aluminum mass fraction of the sublayer is between 0.06 and 0.25.

6. The component of claim 1 , wherein the average chromium mass fraction of the sublayer is between 0.07 and 0.20.

7. The component of claim 1 , wherein the average hafnium mass fraction of the sublayer is less than 5%.

8. The component of claim 1 , wherein the average silicon mass fraction of the sublayer is less than 5%.

9. The component of claim 1 , wherein the sublayer further comprises at least one element selected from cobalt, molybdenum, tungsten, titanium, and tantalum.

10. The component of claim 1 , further comprising a thermally insulating ceramic layer covering the protective layer.

11. The component of claim 1 , wherein the thickness of the sublayer is between 5 μm and 50 μm.

12. A process for manufacturing a turbine component comprising:
vacuum deposition of a sublayer of a nickel-based metal superalloy comprising at least aluminum, nickel, chromium, silicon, and hafnium, and having, predominantly in volume, a γ′-Ni3Al phase, as well as optionally a γ-Ni phase, on a substrate of single-crystal nickel-based superalloy comprising rhenium and having a γ-γ′ Ni phase and an average chromium mass fraction of less than 0.08; and
formation of an aluminum oxide protective layer on the sublayer.

13. The process of claim 12 , wherein the vacuum deposition is carried out by a method selected from physical vapor deposition, thermal spraying, joule evaporation, pulsed laser ablation and sputtering.

14. The process as claimed in claim 12 , wherein the sublayer is deposited by at least one of co-spraying and co-evaporating targets of different metallic materials.

Assignees

• Safran

Inventors

• Saboundji Amar
• Jaquet Virginie

Classifications

• F01D25/005

  Selecting particular materials · CPC title

• F01D5/288 Primary

  Protective coatings for blades · CPC title

• F05D2230/313

  by physical vapour deposition · CPC title

• F05D2300/175

  Superalloys · CPC title

• F05D2260/231

  Preventing heat transfer · CPC title