Machinable coating with thermal protection
AssigneeRaytheon Technologies Corporation
InventorsDaniel S. Rogers, Robert A. White, III
Life of this patent
Estimating the term…
Abstract
A section of a gas turbine engine includes a ceramic component and a metallic component situated adjacent the ceramic component. The ceramic component and the metallic component are situated outside of a core flow path of the gas turbine engine. The section of a gas turbine engine also includes an interface between the ceramic component and a metallic component and a mullite-based coating disposed at the interface. The coating provides thermal protection to the ceramic component and the metallic component, and provides thermochemical protection against interaction between the ceramic component and the metallic component. A gas turbine engine and a method of protecting components in a gas turbine engine are also disclosed.
Claims20
A section of a gas turbine engine, comprising:
- a ceramic component;
- a metallic component situated adjacent the ceramic component, wherein the ceramic component and the metallic component are situated outside of a core flow path of the gas turbine engine;
- an interface between the ceramic component and a metallic component;
- and
- a mullite-based coating disposed at the interface, the coating providing thermal protection to the ceramic component and the metallic component, and providing thermochemical protection against interaction between the ceramic component and the metallic component, wherein the coating is machinable to smooth a surface of the coating or reduce a thickness of the coating.
A gas turbine engine, comprising:
- a metallic engine casing structure;
- a ceramic component attached to the metallic engine casing structure;
- a mullite-based coating disposed on at least one of the metallic engine casing structure and the ceramic component, the coating providing thermal protection to at least one of the ceramic component and the metallic casing structure, and providing thermochemical protection against interaction between the ceramic component and the metallic engine causing structure, wherein the coating is machinable to smooth a surface of the coating or reduce a thickness of the coating.
A method of protecting components in a gas turbine engine, comprising:
- disposing a mullite-based coating at an interface between a metallic component and a ceramic component in a gas turbine engine, wherein the ceramic component and the metallic component are situated outside of a core flow path of the gas turbine engine, the coating providing thermal protection to the ceramic component and the metallic component, and providing thermochemical protection against interaction between the ceramic component and the metallic component, and further comprising machining the coating to smooth a surface of the coating or reduce a thickness of the coating.
Dependencies are inferred from the claim text.