Abstract: A gas turbine engine system is provided. The gas turbine engine system includes a gas turbine engine and an exhaust gas conditioning system. The gas turbine engine includes at least one combustion chamber and at least one turbine downstream from the combustion chamber. The combustion chamber is coupled in flow communication to a source of hydrocarbonaceous fuel and to a source of oxygen. The gas turbine engine is operable with a working fluid that is substantially nitrogen-free. The exhaust gas conditioning system is coupled between a discharge outlet of the gas turbine engine and an inlet of the gas turbine engine.

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: A gas turbine engine system is provided. The gas turbine engine system includes a gas turbine engine, an exhaust gas conditioning system, and a sequestration chamber. The gas turbine engine includes at least one compressor, at least one combustion chamber downstream from the compressor, and at least one turbine downstream from the combustion chamber. The combustion chamber is coupled in flow communication to a source of hydrocarbonaceous fuel and to a source of oxygen. The gas turbine engine is operable with a working fluid that is substantially nitrogen-free. The exhaust gas conditioning system is coupled between a discharge outlet and an inlet of the gas turbine engine. The exhaust gas conditioning system receives all of the exhaust discharged from the gas turbine engine. The sequestration chamber stores carbon dioxide and is coupled to the gas turbine engine for receiving working fluid bled from the turbine upstream from combustion chamber.

Abstract: A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector 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. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a centerbody.

Abstract: A process for carrying out chemical reactions in the gas phase or gas-liquid phase comprises feeding the chemical reagents under pressure into the combustion chamber of a turbine engine, where they react to form a desired chemical product. The heat energy evolved in the process can be utilized through the action of the turbine to power auxiliary equipment attached to the turbine engine, such as an electrical generator. In another embodiment, the turbine engine is utilized to carry out at least two reactions: a primary reaction which occurs in the combustion chamber of the engine, and a second reaction which occurs in an augmentor-section of the engine, utilizing the product of the primary reaction as a reagent in the production of a final product.