Carbon deposit inhibiting thermal barrier coating for combustors
AssigneeHoneywell International Inc.
InventorsThomas E. Strangman, Dave Narasimhan, Jeffrey P. Armstrong, Keith R. Karasek
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Abstract
A carbon deposit inhibiting thermal barrier coating for an internal element or component in a gas turbine engine. Such coating includes a layer of thermal barrier material coated onto the surface of an engine component that will be exposed to the flow of burning engine gases. Such coating further includes a layer of carbon deposit inhibiting material coated on top of the layer of thermal barrier material.
Claims21
A carbon deposit inhibiting thermal barrier coating for an element in a gas turbine engine, such coating consisting essentially of:
- a layer of thermal barrier material formed on an exposed surface of a gas turbine engine element exposed to combustion gases;
- a 1 to 50 mil thick, continuous layer of carbon deposit inhibiting material applied on top of the layer of thermal barrier material;
- and
- wherein the carbon deposit inhibiting material is a refractory oxide selected from a group consisting of yttria and lanthanum oxide.
An article for use in a gas turbine engine, such article consisting essentially of:
- a gas turbine engine element having a surface that will be exposed to engine gases and fuel droplets;
- a layer of thermal barrier material coated onto the engine element surface that will be exposed to combustion gases;
- a 1 to 50 mil thick, continuous layer of carbon deposit inhibiting material coated onto the outer surface of the thermal barrier material;
- and
- wherein the carbon deposit inhibiting material is a refractory oxide selected from a group consisting of yttria and lanthanum oxide.
Dependencies are inferred from the claim text.