Turbine component made from superalloy and associated manufacturing method

Patent metadata

Field	Value
Publication number	US-2021062660-A1
Application number	US-201816498836-A
Country	US
Kind code	A1
Filing date	Mar 30, 2018
Priority date	Mar 30, 2017
Publication date	Mar 4, 2021
Grant date	—

Abstract

The invention concerns a turbine component, such as a turbine blade or a distributor fin, for example, comprising a substrate made from single-crystal nickel superalloy, and a metal sublayer covering the substrate, characterised in that the metal sublayer comprises at least two elementary layers, including a first elementary layer and a second elementary layer, the first elementary layer being arranged between the substrate and the second elementary layer, each elementary layer comprising a γ′-Ni3Al phase, and optionally a γ-Ni phase, and in that the average atomic fraction of aluminum in the second elementary layer is strictly greater than the average atomic fraction of aluminum in the first elementary layer.

First claim

1 . A turbine component comprising:
a single-crystal nickel-based superalloy substrate, and a metallic bond coat covering the substrate, the metallic bond coat comprising at least two elemental layers, including a first elemental layer and a second elemental layer, the first elemental layer being disposed between the substrate and the second elemental layer, each elemental layer comprising a γ′-Ni 3 Al phase and in that the average atomic fraction of aluminum in the second elemental layer is strictly higher than the average atomic fraction of aluminum in the first elemental layer.

2 . The turbine component of claim 1 , wherein at least one elemental layer comprises a γ-Ni phase.

3 . The turbine component of claim 1 , wherein the average atomic fraction of aluminum in the first elemental layer is strictly higher than the average atomic fraction of aluminum in the substrate.

4 . The turbine component of claim 1 , wherein the first elemental layer comprises a γ′-Ni 3 Al phase and a γ-Ni phase, and the metallic bond coat comprises at least one further elemental layer comprising only a γ-Ni phase.

5 . The turbine component of claim 1 , wherein the metallic bond coat comprises a plurality of elemental layers, each elemental layer comprising a γ′-Ni 3 Al phase, and possibly a γ-Ni phase, and wherein the average atomic fraction of aluminum in the elemental layers increases with distance from the substrate.

6 . The turbine component of claim 1 , wherein the average atomic fraction of aluminum in the elemental layer furthest from the substrate is between 0.22 and 0.35.

7 . to the turbine component of claim 1 , wherein the average atomic fraction of aluminum in the elemental layer closest to the substrate is less than 0.2.

8 . The turbine component of claim 1 , wherein the difference between the average atomic fraction of aluminum in the substrate and the average atomic fraction of aluminum in the elemental layer closest to the substrate is less than 0.08.

9 . The turbine component of claim 1 , wherein the difference between the average atomic fraction of aluminum in two successive elemental layers is less than 0.06.

10 . The turbine component of claim 1 , wherein each elemental layer comprises at least one additive selected from chromium and hafnium, and wherein the average atomic fraction of additive in the elemental layers increases with distance from the substrate.

11 . The turbine component of claim 10 , wherein each elemental layer comprises hafnium, and wherein the difference between the average atomic fraction of hafnium in two successive elemental layers is less than 0.001.

12 . The turbine component of claim 10 , wherein the average atomic fraction of hafnium in the elemental layer furthest from the substrate is less than 0.03 and the average atomic fraction of hafnium in the elemental layer nearest the substrate is greater than 0.0005.

13 . Process for fabricating a turbine component comprising steps of:
a) deposition of a first elemental layer comprising a γ′-Ni 3 Al phase, and possibly a γ-Ni phase, and having an average atomic fraction of aluminum xi, on a single-crystal nickel-based metallic superalloy substrate; b) deposition of a second elemental layer comprising a γ′-Ni 3 Al phase, and possibly a γ-Ni phase, and having an average atomic fraction of aluminum x 2 strictly greater than x 1 on the first elemental layer.

14 . The process of claim 13 , wherein the first elemental layer has an average atomic fraction of aluminum xi strictly higher than the average atomic fraction of aluminum x 0 in the nickel-based superalloy of the substrate.

Assignees

• Safran

Inventors

• Saboundji Amar
• Jaquet Virginie

Classifications

• F01D5/28

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• C23C30/00

  Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process (C23C26/00, C23C28/00 take precedence) · CPC title

• C23C28/02

  only coatings {only including layers} of metallic material · CPC title

• C23C14/16

  on metallic substrates or on substrates of boron or silicon · CPC title

• C23C28/36

  including layers graded in composition or physical properties · CPC title