Segmented ceramic coating interlayer

Patent metadata

Field	Value
Publication number	US-2016251970-A1
Application number	US-201415026747-A
Country	US
Kind code	A1
Filing date	Sep 17, 2014
Priority date	Oct 2, 2013
Publication date	Sep 1, 2016
Grant date	—

Abstract

A turbine article includes a substrate with a geometric surface feature having a plurality of recesses recessed into the substrate. A ceramic topcoat is disposed over the geometric surface feature. The topcoat includes portions that are separated by faults extending through the topcoat from the geometric surface feature so the topcoat is segmented. A ceramic interlayer is disposed between the topcoat and the geometric surface feature.

First claim

What is claimed is:

1 . A turbine article comprising:
a substrate with a geometric surface feature having a plurality of recesses recessed into the substrate; a ceramic topcoat disposed over the geometric surface feature, the topcoat including portions that are separated by faults extending through the topcoat from the geometric surface feature so the topcoat is segmented; and a ceramic interlayer disposed between the topcoat and the geometric surface feature.

2 . A turbine article as recited in claim 1 , wherein the interlayer is a toughened ceramic interlayer.

3 . A turbine article as recited in claim 1 , wherein the ceramic interlayer is disposed between the topcoat and a bond coat disposed inboard of the substrate.

4 . A turbine article as recited in claim 1 , wherein the ceramic interlayer is 2.54×10 −6 to 7.62×10 −5 meters (0.1 to 3.0 mils) thick.

5 . A turbine article as recited in claim 1 , wherein each of the recesses includes a substantially uniform recess depth extending into the substrate and recess width, wherein the ratio of the recess width to the recess depth is 1 to 10, with the recess depth being at least 0.01 inches (0.254 millimeters).

6 . A turbine article as recited in claim 1 , wherein the substrate is metallic.

7 . A turbine article comprising:
a substrate with a geometric surface feature having a plurality of recesses recessed into the substrate; a ceramic topcoat disposed over the geometric surface feature, the topcoat including portions that are separated by faults extending through the topcoat from the geometric surface feature; a ceramic interlayer disposed between the topcoat and the geometric surface feature; and an erosion resistant thermal barrier coating (E-TBC) layer between the topcoat and the interlayer.

8 . A turbine article as recited in claim 7 , wherein the interlayer is disposed between the topcoat and a bond coat disposed inboard of the substrate.

9 . A turbine article as recited in claim 7 , wherein the erosion resistant thermal barrier coating (E-TBC) layer is 2.54×10 −5 to 3.81×10 −4 (1.0 to 15 mils) thick.

10 . A turbine article as recited in claim 7 , wherein the erosion resistant thermal barrier coating (E-TBC) layer includes a material including at least one of yttrium stabilized zirconium and gadolinia zirconate.

11 . A turbine article as recited in claim 7 , wherein the interlayer includes a material including at least one of yttrium stabilized zirconium and gadolinia zirconate.

12 . A turbine article as recited in claim 7 , wherein the topcoat includes a material including at least one of yttrium stabilized zirconium and gadolinia zirconate.

Assignees

• United Technologies Corp

Inventors

• Strock Christopher W
• Lutjen Paul M

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2300/5023

  Thermal capacity · CPC title

• F05D2300/2118

  Zirconium oxides · CPC title