Abstract: A gas turbine component includes a substrate and a corrosion resistant layer coupled to the substrate. The corrosion resistant layer includes zirconium silicate and is configured to protect the substrate from exposure to a vanadium corrodent.

Abstract: A thermal barrier coating composition comprises: A. a binder in an amount from about 1% wt. % to about 15 wt. % and: B. a zirconia-containing powder comprising: I. up to about 65 wt. % of a component comprising: a. a first metal oxide selected from the group including ytterbia, neodymia, mixtures of ytterbia and neodymia, mixtures of ytterbia and lanthana, mixtures of neodymia and lanthana, and mixtures of ytterbia, neodymia and lanthana in an amount of from about 8 wt. % to about 55 wt. % of the component; and b. a second metal oxide selected from the group including yttria, calcia, ceria, scandia, magnesia, india and mixtures thereof in an amount up to about 2 wt. % or less of the component; and II. one or more of a third metal oxide selected from the group including: a. hafnia in an amount up to about 2 wt. % or less of the component; and b. tantala in an amount up to about 2 wt. % or less of the component; and and a balance zirconia by weight.

Abstract: A gas turbine component includes a substrate and a corrosion resistant layer coupled to the substrate. The corrosion resistant layer includes zirconium silicate and is configured to protect the substrate from exposure to a vanadium corrodent.

Abstract: A treatment composition is disclosed including a carrier and a sacrificial oxide-forming material suspended within the carrier. The sacrificial oxide-forming material is selected from the group consisting of tin oxide, magnesium oxide, antimony pentaoxide, and combinations thereof. A treatment process for a gas turbine component including an abradable ceramic coating is disclosed. The process includes contacting the abradable ceramic coating with the treatment composition. The sacrificial oxide-forming material is infused into the abradable ceramic coating to form sacrificial oxide-forming deposits within the abradable ceramic coating. A rejuvenation process is disclosed including contacting the hot gas path surface of a gas turbine component with a rinse composition comprising water and the treatment composition to form the sacrificial oxide-forming deposits within the abradable ceramic coating.

Abstract: A treatment process for a gas turbine component comprising a bond coating and a ceramic coating, an oxide-forming treatment composition, and a treated component are disclosed. The ceramic coating is contacted with a treatment composition. The treatment composition includes a carrier and a particulate oxide-forming material suspended within the carrier. The particulate oxide-forming material is one or more of yttria oxide, antimony, or tin oxide. The treatment composition is heated to form an oxide overlay coating on the ceramic coating. The treated component includes a ceramic coating and one or both of a corrosion inhibitor and an oxide formed by an oxide-forming treatment composition having the corrosion inhibitor.

Abstract: A treatment composition is disclosed including a carrier and a sacrificial oxide-forming material suspended within the carrier. The sacrificial oxide-forming material is selected from the group consisting of tin oxide, magnesium oxide, antimony pentaoxide, and combinations thereof. A treatment process for a gas turbine component including an abradable ceramic coating is disclosed. The process includes contacting the abradable ceramic coating with the treatment composition. The sacrificial oxide-forming material is infused into the abradable ceramic coating to form sacrificial oxide-forming deposits within the abradable ceramic coating. A rejuvenation process is disclosed including contacting the hot gas path surface of a gas turbine component with a rinse composition comprising water and the treatment composition to form the sacrificial oxide-forming deposits within the abradable ceramic coating.

Abstract: A treatment process for a gas turbine component comprising a bond coating and a ceramic coating, an oxide-forming treatment composition, and a treated component are disclosed. The ceramic coating is contacted with a treatment composition. The treatment composition includes a carrier and a particulate oxide-forming material suspended within the carrier. The particulate oxide-forming material is one or more of yttria oxide, antimony, or tin oxide. The treatment composition is heated to form an oxide overlay coating on the ceramic coating. The treated component includes a ceramic coating and one or both of a corrosion inhibitor and an oxide formed by an oxide-forming treatment composition having the corrosion inhibitor.

Abstract: A system includes a catalytic reactor configured to mount to a combustor. The catalytic reactor includes a catalyst configured to reduce emissions associated with combustion in the combustor. The catalytic reactor also includes a first and a second sacrificial coating disposed over the catalyst prior to mounting of the catalytic reactor into the combustor, wherein the first and second sacrificial coatings are removable while the catalytic reactor is mounted to the combustor without damaging the catalyst.

Abstract: A system includes a catalytic reactor configured to mount to a combustor. The catalytic reactor includes a catalyst configured to reduce emissions associated with combustion in the combustor. The catalytic reactor also includes a first sacrificial coating disposed over the catalyst prior to mounting of the catalytic reactor into the combustor, wherein the first sacrificial coating is removable while the catalytic reactor is mounted to the combustor without damaging the catalyst.

Abstract: A coating process, a coating, and a coated component are disclosed. The coating process includes providing a MCrAlY substrate, applying a thermal barrier coating to the MCrAlY substrate, applying a flash layer to the thermal barrier coating, the flash layer including an inert ceramic, applying a reaction product deposition onto the thermal barrier coating, the reaction product deposition including reaction products selected from the group consisting of a magnesium oxide compound, a magnesium orthovanadate compound, a magnesium vanadate compound, a magnesium pyrovanadate compound, a magnesium sulfate compound, and combinations thereof. The reaction products are by-products of a doped fuel.

Abstract: A method for applying a protective coating to gas turbine engine components using a saturated solution of nickel acetate tetrahydrate, applying a uniform thickness of the coating onto the thermal barrier coating of selected components, and heat treating the coated component in air at a temperature sufficient to form a protective layer of NiO. The saturated NiO solution has sufficient solubility to penetrate into the microscopic cracks of the thermal barrier coating to form a “sacrificial mitigation layer” of NiO that substantially inhibits the reaction between vanadium pentoxide and yttria-stabilized compounds present in the thermal barrier coating.