Turbine part made of superalloy comprising rhenium and/or ruthenium and associated manufacturing method

Patent metadata

Field	Value
Publication number	US-2020248562-A1
Application number	US-201816649397-A
Country	US
Kind code	A1
Filing date	Sep 21, 2018
Priority date	Sep 21, 2017
Publication date	Aug 6, 2020
Grant date	—

Abstract

A turbine part, such as a turbine blade or a distributor fin, for example, including a substrate made of superalloy based on monocrystalline nickel, including rhenium and/or ruthenium, and having a γ′-NisAI phase that is predominant by volume and a γ-Ni phase, the part also including a sublayer made of metal superalloy based on nickel covering the substrate, wherein the sublayer has a γ′-NisAI phase that is predominant by volume and wherein the sublayer has an average atomic fraction of aluminium of between 0.15 and 0.25, of chromium of between 0.03 and 0.08, of platinum of between 0.01 and 0.05, of hafnium of less than 0.01 and of silicon of less than 0.01. A process for manufacturing a turbine part including a step of vacuum deposition of a sublayer made of a superalloy based on nickel having predominantly by volume a γ′-NisAI phase, on a substrate made of superalloy based on nickel including rhenium and/or ruthenium.

First claim

1 . A turbine part comprising a substrate made of a single-crystal nickel-base superalloy, comprising rhenium and/or ruthenium, and having a γ′-Ni 3 Al phase which is predominant in volume and a γ-Ni phase, and a bond coat made of a nickel-based metal superalloy covering the substrate, wherein the bond coat has a γ′-Ni 3 Al phase of majority volume and wherein the bond coat has an average atomic fraction:
of aluminum between 0.15 and 0.25;
of chromium between 0.03 and 0.08:
of platinum between 0.01 and 0.05;
of hafnium less than 0.01 and
of silicon less than 0.01.

2 . The part as claimed in claim 1 , wherein the bond coat has a γ′-Ni 3 Al phase greater than 95% by volume.

3 . The part as claimed in claim 1 , wherein the bond coat has a γ′-Ni 3 Al phase and a β-NiAlPt phase.

4 . The part as claimed in claim 1 , wherein the bond coat has a γ′-Ni 3 Al phase and a γ-Ni phase.

5 . The part as claimed in claim 1 , wherein the rhenium mass fraction of the substrate is greater than or equal to 0.04.

6 . The part as claimed in claim 1 , wherein the bond coat further comprises at least one element selected from cobalt, molybdenum, tungsten, titanium, tantalum.

7 . The part as claimed in claim 1 , comprising a protective layer of aluminum oxide covering the bond coat.

8 . The part as claimed in claim 7 , comprising a thermally insulating ceramic layer covering the protective layer.

9 . The part as claimed in claim 1 , wherein the thickness of the bond coat is between 5 μm and 50 μm.

10 . A turbine blade which comprises:
a turbine part comprising a substrate made of a single-crystal nickel-base superalloy, comprising rhenium and/or ruthenium, and having a γ′-Ni3Al phase which is predominant in volume and a γ-Ni phase, and a bond coat made of a nickel-based metal superalloy covering the substrate, wherein the bond coat has a γ′-Ni3Al phase of majority volume and wherein the bond coat has an average atomic fraction: of aluminum between 0.15 and 0.25; of chromium between 0.03 and 0.08; of platinum between 0.01 and 0.05: of hafnium less than 0.01 and of silicon less than 0.01.

11 . A gas turbine engine comprising a turbine comprising a turbine blade as claimed in claim 10 .

12 . A process for manufacturing a turbine part comprising a step of vacuum deposition of a bond coat of a nickel-based superalloy having a γ′-Ni 3 Al phase predominantly in volume, on a substrate made of a nickel-based superalloy comprising rhenium and/or ruthenium, the bond coat having an average atomic fraction:
of aluminum between 0.15 and 0.25;
of chromium between 0.03 and 0.08;
of platinum between 0.01 and 0.05;
of hafnium less than 0.01 and
of silicon less than 0.01.

13 . The process as claimed in claim 12 , wherein the 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 bond coat is deposited by co-spraying and/or co-evaporating metal targets.

Assignees

• Safran

Inventors

• Saboundji Amar
• Jaquet Virginie

Classifications

• F01D5/288 Primary

  Protective coatings for blades · CPC title

• F05D2300/607

  Monocrystallinity · CPC title

• F05D2300/182

  Metal-aluminide intermetallic compounds · CPC title

• F05D2300/1432

  Ruthenium · CPC title

• F05D2300/143

  Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd · CPC title