Components having coating systems defined by tiles secured thereto, methods of producing the components, and aircraft comprising the components
AssigneeHoneywell International Inc.
InventorsBahram Jadidian, Kevin Blinn, Mehrad Mehr
Life of this patent
Estimating the term…
Abstract
Components of gas turbine engines, aircraft comprising the components, and methods of producing the components are provided. The component includes a surface, and a set of tiles secured to the surface at interfaces between the set of tiles and the surface and between each of the set of tiles. The set of tiles conform to the surface and in combination define a coating system on the surface that includes an environmental barrier coating and/or a thermal barrier coating.
Claims20
A component for a gas turbine engine, comprising:
- a surface;
- and
- a set of tiles secured to the surface at first interfaces between the set of tiles and the surface and secured at second interfaces between each of the set of tiles, wherein the set of tiles conform to the surface, wherein the set of tiles in combination define a coating system on the surface that includes an environmental barrier coating and/or a thermal barrier coating, wherein the surface includes a silicon-based ceramic material and the set of tiles include one or more rare earth silicate materials, wherein gaps are provided in at least some of the first interfaces between the set of tiles and the surface that are configured to provide for relative movement between the set of tiles and the surface and thereby provide stress relief to the coating system.
A method for providing a coating system on a component of a gas turbine engine, the method comprising:
- forming a set of tiles;
- and
- joining the set of tiles to a surface of the component by securing the tiles at first interfaces between the set of tiles and the surface and securing the tiles at second interfaces between each of the set of tiles, wherein the set of tiles in combination define the coating system on the surface that includes an environmental barrier coating and/or a thermal barrier coating, wherein the surface of the component includes a silicon-based ceramic material and the set of tiles include one or more rare earth silicate materials;
- and
- providing gaps in at least some of the first interfaces between the set of tiles and the surface of the component that are configured to provide for relative movement between the set of tiles and the surface and thereby provide stress relief to the coating system.
An aircraft that includes a gas turbine engine, the aircraft comprising:
- a component of the gas turbine engine that includes a surface that includes a silicon-based ceramic material;
- and
- a set of tiles secured to the surface of the component at first interfaces between the set of tiles and the surface of the component and secured at second interfaces between each of the set of tiles, wherein the set of tiles conform to the surface of the component, wherein the set of tiles in combination define a coating system on the surface of the component that includes an environmental barrier coating and/or a thermal barrier coating, wherein the coating system includes at least one layer having a rare earth silicate material, wherein gaps are provided in at least some of the first interfaces between the set of tiles and the surface that are configured to provide for relative movement between the set of tiles and the surface and thereby provide stress relief to the coating system.
Dependencies are inferred from the claim text.