Abstract: Methods of making components having calcium magnesium aluminosilicate (CMAS) mitigation capability include providing a component, applying an environmental barrier coating to the component, where the environmental barrier coating includes a CMAS mitigation composition selected from the group consisting of zinc aluminate spinel, alkaline earth zirconates, alkaline earth hafnates, rare earth gallates, beryl, and combinations thereof.

Abstract: A method of operating a turbine engine system and a turbine engine system are provided. The method comprises supplying a flow of oxygen to a combustion chamber defined within a plurality of turbines coupled serially together within the turbine engine system, supplying a flow of hydrocarbonaccous fuel to the combustion chambers of each of the plurality of turbines in the turbine engine system, and supplying a working fluid to an inlet of a first turbine engine coupled within the turbine engine system, wherein the working fluid is substantially nitrogen-free and wherein each of the turbines coupled within the turbine engine system is operable with the resulting fuel-oxygen-working fluid mixture.

Abstract: Methods of making components having calcium magnesium aluminosilicate (CMAS) mitigation capability including providing a component; applying an environmental barrier coating to the component, the environmental barrier coating having a separate CMAS mitigation layer including a CMAS mitigation composition selected from the group consisting of zinc aluminate spinel, alkaline earth zirconates, alkaline earth hafnates, rare earth gallates, beryl, and combinations thereof.

Abstract: Environmental barrier coatings having CMAS mitigation capability for silicon-containing components. In one embodiment, the barrier coating includes a bond coat layer comprising aluminide-alumina TGO; and an outer layer selected from the group consisting of AeAl2O19, AeHfO3, AeZrO3, ZnAl2O4, MgAl2O4, Ln4Al2O9, Lna4Ga2O9, Ln3Al5O12, Ln3Ga5O12, Ga2O3, HfO2, and LnPO4.

Abstract: Environmental barrier coatings having CMAS mitigation capability for silicon-containing components. In one embodiment, the barrier coating includes a bond coat layer comprising silicon or silicide, and an outer layer selected from the group consisting of Ln4Al2O9, and Lna4Ga2O9.

Abstract: Environmental barrier coating having CMAS mitigation capability for oxide components. In one embodiment, the barrier coating includes an outer layer selected from AeAl2O19, AeHfO3, AeZrO3, ZnAl2O4, MgAl2O4, Ln4Al2O9, Lna4Ga2O9, Ln3Al5O12, Ln3Ga5O12, and Ga2O3.

Abstract: A protected article is prepared by providing the article, depositing a bond coat onto an exposed surface of the article, and producing a thermal barrier coating on an exposed surface of the bond coat. The step of producing the thermal barrier coating includes the steps of depositing a primary ceramic coating onto an exposed surface of the bond coat, and depositing a stabilization composition onto an exposed surface of the primary ceramic coating. The stabilization composition includes a first element selected from Group 2 or Group 3 of the periodic table, and a second element selected from Group 5 of the periodic table. The atomic ratio of the amount of the first element to the amount of the second element is at least 1.3, more preferably at least 1:1.

Abstract: An article is prepared by furnishing a plurality of powder particle substrates made of a substrate metal, providing a nonmetallic precursor of a metallic coating material, wherein the metallic coating material comprises an alloying element that is thermophysically melt incompatible with the substrate metal, contacting the powder particle substrates with the nonmetallic precursor, chemically reducing the nonmetallic precursor to form coated powder particles comprising the powder particle substrates having a surface-enriched layer of the metallic coating material thereon without melting the powder particle substrates, and processing the coated powder particles to form the article, without melting the powder particle substrates.

Abstract: Environmental barrier coating having CMAS mitigation capability for oxide components. In one embodiment, the barrier coating includes an outer layer selected from AeAl2O19, AeHfO3, AeZrO3, ZnAl2O4, MgAl2O4, Ln4Al2O9, Lna4Ga2O9, Ln3A15O12, Ln3Ga5O12, and Ga2O3.

Abstract: Methods of making components having calcium magnesium aluminosilicate (CMAS) mitigation capability including providing a component; applying an environmental barrier coating to the component, the environmental barrier coating having a separate CMAS mitigation layer including a CMAS mitigation composition selected from the group consisting of zinc aluminate spinel, alkaline earth zirconates, alkaline earth hafnates, rare earth gallates, beryl, and combinations thereof.

Abstract: Environmental barrier coatings having CMAS mitigation capability for silicon-containing components. In one embodiment, the barrier coating includes a bond coat layer comprising aluminide-alumina TGO; and an outer layer selected from the group consisting of AeAl2O19, AeHfO3, AeZrO3, ZnAl2O4, MgAl2O4, Ln4Al2O9, Lna4Ga2O9, Ln3Al5O12, Ln3Ga5O12, Ga2O3, HfO2, and LnPO4.

Abstract: Environmental barrier coatings having CMAS mitigation capability for silicon-containing components. In one embodiment, the barrier coating includes a bond coat layer comprising silicon or silicide, and an outer layer selected from the group consisting of Ln4Al2O9, and Lna4Ga2O9.

Abstract: Calcium magnesium aluminosilcate (CMAS) mitigation compositions selected from zinc aluminate spinel, alkaline earth zirconates, alkaline earth hafnates, rare earth gallates, beryl, and combinations thereof wherein the CMAS mitigation composition is included as a separate CMAS mitigation layer in an environmental barrier coating for a high temperature substrate component.

Abstract: A coated fan rotor blade and method for coating a fan rotor blade. The coated fan rotor blade includes a fan rotor blade; and a coating disposed on said fan rotor blade. The coating comprises a binder; and a filler made up of a plurality of particles. The filler material is incorporated into the binder material, and the particles in the filler interact to produce vibrational damping. In particular, the coating includes small, dense, flattened particles or plates that are incorporated into a thin layer of visco-elastic material, such as rubber, silicone, fluoro-elastomer, or urethane and bonded to the surface of the rotor blade to provide damping of high frequency excitation.

Abstract: Methods for coating a turbine engine rotor component involving depositing at least one platinum group metal selected from platinum, palladium, rhodium, ruthenium, iridium and osmium on the rotor component, and heating the rotor component to a temperature of from about 500° C. to about 800° C.

Abstract: A coating system for reducing the tendency for hydrocarbon fluids, such as fuels and oils, to form carbonaceous deposits that adhere to fluid containment surfaces. The coating system combines an outermost layer of platinum with an inner ceramic barrier layer of silica and/or tantala. The platinum layer catalyzes the hydrocarbon fluid to form particles of carbonaceous gum substances, and the ceramic barrier layer seals the containment surface from the hydrocarbon fluid to eliminate attachments points for deposits and inhibit interdiffusion between the platinum layer and the containment surface. The invention also encompasses a coating apparatus and process for depositing the coating system.

Abstract: A coating system and method for reducing the tendency for hydrocarbon fluids, such as fuels and oils, to form carbonaceous deposits that adhere to a wall of a containment article. Of particular concern are carbonaceous deposits that form at temperatures below about 650° F. (about 345° C.). The coating system combines an outermost layer of platinum with a ceramic barrier layer. The coating system significantly reduces the formation of carbonaceous deposits and the adhesion of such deposits. To further reduce wall and hydrocarbon fluid temperatures and formation of carbonaceous deposits, the coating system is preferably applied to the surface of the wall wetted by the fluid, as well as the opposite surface of the wall exposed to a surrounding environment. The outermost layers serve as radiation shields to reduce heat transfer from the surrounding environment to the wall, and from the wall to the hydrocarbon fluid.

Abstract: A high temperature gas turbine component for use in the gas flow path that comprises a specular optical reflector coating system. A thin specular optical reflector coating system is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. The thin reflector coating system comprises a thin high temperature and corrosion resistant refractory stabilizing layer, which is applied over a thin reflective metal layer, which is applied over a thin high temperature and corrosion resistant refractory sealing layer.

Abstract: A method for operating an aircraft engine facilitates preventing ice accumulation on the aircraft engine. The method comprises coupling a semi-permeable membrane to the engine adjacent an outer surface of the engine, coupling a fluid reservoir to the aircraft engine in flow communication with the semi-permeable membrane, and supplying fluid from the fluid reservoir to the semi-permeable membrane to facilitate preventing ice accumulation on the aircraft engine outer surface.

Abstract: A method for applying a coating system that is applied to a surface of a component for preventing or at least substantially preventing interdiffusion between the component surface and a protective thermal layer applied to the component surface when the thermal layer is exposed to elevated temperatures. The method includes applying a carrier layer containing aluminum to the component surface. Next, the layer is heated to a first predetermined temperature for a first predetermined period of time in the substantial absence of oxygen to bond the aluminum with the component surface, the heat dissolving the carrier portion of the aluminum layer. The remaining portion of the aluminum layer is then heated to a second predetermined temperature for a second predetermined period of time to form an oxidized aluminum layer. Finally, at least one protective thermal layer is applied over the oxidized aluminum layer.