Coating

Patent metadata

Field	Value
Publication number	US-11512378-B2
Application number	US-202017087202-A
Country	US
Kind code	B2
Filing date	Nov 2, 2020
Priority date	Nov 8, 2019
Publication date	Nov 29, 2022
Grant date	Nov 29, 2022

Abstract

A method of assessing the quality of a bond coat for bonding a ceramic coating to a metallic substrate comprises determining a thresholded summit area for the bond coat.

First claim

We claim:

1. A bond coat for bonding a ceramic coating to a metallic substrate, wherein the bond coat has a thresholded summit area, S sth , of 11% or more, wherein the thresholded summit area, S sth , is given by:

S

s
⁢
t
⁢
h

=

1
A

⁢

∑

i
=
1

n

⁢

S

s
⁢
i

where A is the total surface area sampled, n is the number of thermo-mechanically dominant summits present in the area sampled and S si is the area of an individual thresholded summit.

2. The bond coat according to claim 1 , wherein the bond coat material is a metallic alloy.

3. The bond coat according to claim 2 , wherein the metallic alloy contains aluminum, silicon, or chromium.

4. The bond coat according to claim 1 , wherein the bond coat is applied to the metallic substrate using one or more thermal spraying processes from among air plasma spraying (APS); high velocity oxygen fuel thermal spraying (HVOF); high velocity air fuel spraying (HVAF); low pressure plasma spraying (LPPS)/vacuum plasma spraying (VPS); or cold spraying.

5. A ceramic coating system comprising the bond coat according to claim 1 , wherein the ceramic coating system further comprises:
a metallic substrate; and
a ceramic layer;
wherein the bond coat is formed on the metallic substrate, and the ceramic layer is formed on the bond coat.

6. The ceramic coating system according to claim 5 , wherein the ceramic coating system is a thermal barrier coating system.

7. A component for a gas turbine engine, the component comprising a ceramic coating system according to claim 5 .

8. A gas turbine engine for an aircraft comprising:
an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and
a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft,
wherein a component of the gas turbine engine is a component according to claim 7 .

9. The gas turbine engine according to claim 8 , wherein:
the turbine is a first turbine, the compressor is a first compressor, and the core shaft is a first core shaft;
the engine core further comprises a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor; and
the second turbine, second compressor, and second core shaft are arranged to rotate at a higher rotational speed than the first core shaft.

Assignees

• Rolls Royce Plc

Inventors

• Brewster James G
• Martins Joao P

Classifications

• B32B15/04

  comprising metal as the main or only constituent of a layer, {which is} next to another layer of {the same or of} a {different material (next to a bituminous or tarry layer B32B11/08; next to a water-setting substance layer B32B13/06; next to a glass layer B32B17/061; next to a cellulosic plastic layer B32B23/042)} · CPC title

• G01B11/303

  using photoelectric detection means · CPC title

• F05D2260/231

  Preventing heat transfer · CPC title

• C23C4/129

  Flame spraying · CPC title

• C23C4/134 Primary

  Plasma spraying · CPC title