Thermal barrier coating for edge component
AssigneeRtx Corporation
InventorBrian Cronin
Life of this patent
Estimating the term…
Abstract
A ceramic matric composite (CMC) component for a gas turbine engine, such as blade outer air seal (BOAS), may be shielded from thermal stress. The CMC component includes a first surface configured for exposure to a hot gas stream, a second surface configured for exposure to a cold gas stream, an edge surface of the CMC component disposed between and connecting the first and second surfaces. At least one coating layer is disposed on the first surface and wrapped over the edge surface and the second surface, wherein the at least one coating layer disposed on the second surface has a lower thermal conductivity than the CMC component so as to reduce a thermal gradient between the cooled first surface and the heated second surface.
Claims16
A ceramic matrix composite (CMC) component for a gas turbine engine, comprising:
- a first surface of the CMC component, the first surface configured for exposure to a hot gas stream;
- a second surface of the CMC component disposed opposite the first surface, the second surface configured for exposure to a cold gas stream;
- an edge surface of the CMC component disposed between and connecting the first and second surfaces;
- and
- at least one coating layer,
- wherein at least one layer of the at least one coating layer is applied on the first surface, at least one layer of the at least one coating layer is applied on the edge surface and at least one layer of the at least one coating layer is applied on the second surface,
- wherein the at least one layer of the at least one coating layer applied to the second surface has a lower thermal conductivity than the CMC component, and
- wherein the at least one layer of the at least one coating layer applied to the edge surface comprises an abradable coating layer wrapping over the edge surface.
A method of thermally shielding a ceramic matric composite (CMC) component for a gas turbine engine to reduce thermal stress, comprising:
- applying at least one layer of at least one coating layer to a first surface of the CMC component, the first surface configured for exposure to a hot gas stream;
- applying at least one layer of the at least one coating layer to an edge surface of the CMC component disposed between and connecting the first surface and a second surface of the CMC component;
- and
- applying at least one layer of the at least one coating layer to the second surface, the second surface disposed opposite the first surface and configured for exposure to a cold gas stream,
- wherein the at least one layer of the at least one coating layer applied to the second surface has a lower thermal conductivity than the CMC component, and
- wherein the at least one layer of the at least one coating layer applied to the edge surface comprises an abradable coating layer wrapping over the edge surface.
A method of thermally shielding a ceramic matric composite (CMC) blade outer air seal (BOAS) for a gas turbine engine to reduce thermal stress, comprising:
- applying at least one layer of at least one coating layer to a first surface of the CMC BOAS, the first surface configured for exposure to a hot gas stream;
- applying at least one layer of the at least one coating layer to an edge surface of the CMC BOAS disposed between and connecting the first surface and a second surface of the CMC BOAS;
- and
- applying at least one layer of the at least one coating layer to the second surface, the second surface disposed opposite the first surface and configured for exposure to a cold gas stream,
- wherein the at least one layer of the at least one coating layer applied to the second surface has a lower thermal conductivity than the CMC BOAS, and
- wherein the at least one layer of the at least one coating layer applied to the edge surface comprises an abradable coating layer wrapping over the edge surface.
Dependencies are inferred from the claim text.