Internally cooled ni-base superalloy component with spallation-resistant tbc system

Patent metadata

Field	Value
Publication number	US-2017198601-A1
Application number	US-201614993140-A
Country	US
Kind code	A1
Filing date	Jan 12, 2016
Priority date	Jan 12, 2016
Publication date	Jul 13, 2017
Grant date	—

Abstract

A gas turbine engine component comprising a nozzle segment, the nozzle segment comprising at least one substrate having a surface. A metallic bondcoat is coupled to the surface of the substrate. An yttria-stabilized zirconia thermal barrier coating is coupled to the metallic bondcoat opposite the surface.

First claim

What is claimed is:

1 . A method for providing a component with a coating system comprising the steps of:
providing an air cooled component having a substrate; applying a metallic bondcoat to said substrate; and depositing a layer of an yttria-stabilized zirconia thermal barrier coating on the bondcoat.

2 . The method according to claim 1 , wherein said metallic bondcoat applying step comprises applying a metallic bondcoat selected from the group consisting of a platinum-aluminide coating and an aluminide coating.

3 . The method according to claim 2 , wherein said metallic bondcoat applying step comprises applying a metallic bondcoat wherein said metallic bondcoat has a composition consisting of 1.0 to 18 wt % cobalt, 3.0 to 18 wt % chromium, 5.0 to 15 wt % aluminum, 0.01 to 1.0 wt % yttrium, 0.01 to 0.6 wt % hafnium, 0.0 to 0.3 wt % silicon, 0.1 to 1.0 wt % zirconium, 0.0 to 10 wt % tantalum, 2.5-5.0 wt % tungsten, 0.0 to 10 wt % molybdenum, 23.0 to 27.0 wt % platinum, and the balance nickel.

4 . The method according to claim 1 , wherein said yttria-stabilized zirconia coating depositing step comprises depositing a material containing from 4.0 to 25 wt % yttria.

5 . The method according to claim 1 , wherein said air cooled component providing step comprises providing a substrate formed from a nickel based alloy.

6 . The method according to claim 1 , wherein said yttria-stabilized zirconia coating depositing step comprises depositing a material consisting of from 4.0 to 25 wt % yttria and the balance zirconia.

7 . The method according to claim 1 , wherein said air cooled component comprises a nozzle segment.

8 . The method of claim 7 , wherein said nozzle segment is selected from the group consisting of a singlet, a doublet and a triplet.

9 . The method of claim 1 , further comprising:
installing said air cooled component in a high pressure turbine section of a gas turbine engine.

10 . A gas turbine engine component comprising:
a nozzle segment, said nozzle segment comprising at least one substrate having a surface; a metallic bondcoat coupled to said surface of said substrate; and an yttria-stabilized zirconia thermal barrier coating coupled to said metallic bondcoat opposite said surface.

11 . The gas turbine engine component according to claim 10 , wherein said metallic bondcoat is selected from the group consisting of a platinum-aluminide coating and an aluminide coating.

12 . The gas turbine engine component according to claim 10 , wherein said metallic bondcoat has a composition consisting of 1.0 to 18 wt % cobalt, 3.0 to 18 wt % chromium, 5.0 to 15 wt % aluminum, 0.01 to 1.0 wt % yttrium, 0.01 to 0.6 wt % hafnium, 0.0 to 0.3 wt % silicon, 0.1 to 1.0 wt % zirconium, 0.0 to 10 wt % tantalum, 2.5-5.0 wt % tungsten, 0.0 to 10 wt % molybdenum, 23.0 to 27.0 wt % platinum, and the balance nickel.

13 . The gas turbine engine component according to claim 10 , wherein said yttria-stabilized zirconia coating comprises a material containing from 4.0 to 25 wt % yttria.

14 . The gas turbine engine component according to claim 10 , wherein said yttria-stabilized zirconia coating comprises a material consisting of from 4.0 to 25 wt % yttria and the balance zirconia.

15 . The gas turbine engine component according to claim 10 , wherein said nozzle segment is selected from the group consisting of a singlet, a doublet and a triplet.

16 . The gas turbine engine component according to claim 10 , wherein said nozzle segment is configured air cooled.

Assignees

• United Technologies Corp

Inventors

• Task Michael N
• Boeke Mark A
• Levine Jeffrey R
• Bergman Russell J

Classifications

• F05D2230/313

  by physical vapour deposition · CPC title

• C23C28/3215

  at least one MCrAlX layer · CPC title

• F05D2220/32

  in gas turbines · CPC title

• C23C28/321

  with at least one metal alloy layer · CPC title

• F05D2300/182

  Metal-aluminide intermetallic compounds · CPC title