Abstract: The invention relates to a method and a device for generating electrical energy in a combined system consisting of a power plant and an air handling system. The power plant comprises a first gas expansion unit connected to a generator. The air handling system comprises an air compression unit, a heat exchange system, and a fluid tank. In a first operating mode, feed air is compressed in the air compression unit and cooled in the heat exchange system. A storage fluid is generated from the compressed and cooled feed air and is stored as cryogenic fluid in fluid tank. In a second operating mode, cryogenic fluid is removed from fluid tank and is vaporized, or pseudo-vaporized, at superatmospheric pressure. The gaseous high pressure storage fluid generated is expanded in the gas expansion unit. Gaseous natural gas is introduced into the heat exchange system (21) to be liquefied.

Abstract: A combustor basket assembly for a gas turbine engine that includes a combustor basket having a basket liner including an input end and an output end. A double-wall exit cone is mounted to the output end of the basket liner, where the exit cone includes an inner wall and an outer wall defining an exit cone channel therebetween. A splash plate is mounted to the outer wall to define a splash plate channel between the splash plate and the basket liner. A series of pairs of cooling feed holes are provided through the basket liner, where one of the feed holes in each pair provides cooling air to the cone channel and the other feed hole provides cooling air to the splash plate channel. The outer surface of the outer wall and the inner surface of the inner wall are coated with a thermal barrier coating.

Abstract: The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of an electrical grid. Improvements in power augmentation and engine operation include systems and methods for providing rapid response given a change in electrical grid.

Abstract: A gas turbine combustor having a burner including a plurality of fuel nozzles for injecting fuel, air hole plates positioned on a downstream side of the fuel nozzles and a plurality of air holes arranged in pairs with each of the fuel nozzles, and a combustion chamber for mixing fuel injected from the fuel nozzles and air injected from the air holes and injecting and burning the mixed fuel. Each of the fuel nozzles configuring the burners is provided with a projection in which a part of an outer edge of a section of the fuel nozzle is protruded outward; and the projection is arranged so as to be directed toward a center of the gas turbine combustor. The projection of the fuel nozzle is positioned on a downstream side of a flow of combustion air flowing around each of the fuel nozzles.

Abstract: A jet noise suppressor including a nozzle having a front end and an opposed rear end, spokes extending radially inward from the nozzle, the spokes defining vents, and a center-body connected to the spokes and in fluid communication with the vents, the center-body being positioned centrally within the nozzle and including a closed front end and an open rear end, wherein the front end of the nozzle entrains a first ambient airflow passing through the nozzle and exiting the rear end of the nozzle proximate a periphery of the nozzle, and wherein the vents entrain a second ambient airflow passing through the center-body and exiting the rear end of the nozzle proximate a center of the nozzle.

Abstract: A system includes a gas turbine engine configured to combust an oxidant and a fuel to generate an exhaust gas, a catalyst bed configured to treat a portion of the exhaust gas from the gas turbine engine to generate a treated exhaust gas, a differential temperature monitor configured to monitor a differential temperature between a first temperature of the portion of exhaust gas upstream of the catalyst bed and a second temperature of the treated exhaust gas downstream of the catalyst bed, and an oxidant-to-fuel ratio system configured to adjust a parameter to maintain an efficacy of the catalyst bed based at least in part on the differential temperature in order to maintain a target equivalence ratio.

Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The air passageway has a swirl-inducing relief defined at an exit lip of an outer wall of the air passageway. A gas turbine engine and a method of inducing swirl in an air passageway of a fuel nozzle of a gas turbine engine are also presented.

Abstract: A method for determining an estimate of the specific gravity of a fuel for a gas turbine engine is disclosed. The gas turbine engine includes a fuel control valve and one or more fuel injectors. The method includes determining a first estimate of the specific gravity based on an orifice flow model of the fuel control valve. The method also includes determining a second estimate of the specific gravity based on a combined orifice flow model of the one or more fuel injectors. The method further includes recursively filtering the first estimate and the second estimate to determine a third estimate of the specific gravity.

Abstract: A premix fuel nozzle assembly includes a center body, a pilot premix fuel nozzle assembly that extends axially through the center body and that includes a premix tip having a plurality of premix tubes that each defines a premix passage and a fuel port. The premix passage of each premix tube is in fluid communication with the pilot air passage. The premix fuel nozzle assembly further includes a purge air cartridge assembly that extends axially within the pilot air passage. The purge air cartridge assembly includes a feed tube portion and a tip portion that define a purge air passage within the pilot air passage. The tip portion comprises an aft wall that extends at least partially through an opening defined by the premix tip. The aft wall includes a single axially extending orifice that is in fluid communication with the purge air passage.

Abstract: This invention concerns a method of delivering fuel to an aircraft engine 60, which involves providing a plurality of distinct fuel sources 20, 22, a first fuel source 20 comprising a first fuel having a first aromatic content and a second fuel source 22 comprising a second fuel having a second aromatic content. One or more ambient atmospheric condition is determined for at least a portion of a flight path of the aircraft, said condition being indicative of a likelihood of contrail 135 formation by the engine 60. A desirous fuel composition for combustion by the engine is determined based upon the one or more ambient atmospheric condition and a ratio of the first and second fuels from said respective fuel sources is selected according to said desirous fuel composition. The selected ratio of the first and second fuels is delivered to the aircraft engine 60.