Abstract: The present disclosure relates to systems and methods useful for power production. In particular, a power production cycle utilizing CO2 as a working fluid may be configured for simultaneous hydrogen production. Beneficially, substantially all carbon arising from combustion in power production and hydrogen production is captured in the form of carbon dioxide. Further, produced hydrogen (optionally mixed with nitrogen received from an air separation unit) can be input as fuel in a gas turbine combined cycle unit for additional power production therein without any atmospheric CO2 discharge.

Abstract: The invention relates to a concentric gas flow mixer in a multiple-flow turbomachine, comprising a nominally cylindrical upstream part and a downstream part having outer and inner lobes distributed peripherally around the tower of said mixer, characterised in that it comprises at least one modified lobe having a wall thickness, in at least one area, which is different from the other lobes, so as to modify the vibratory response of said mixer.

Abstract: A fuel control device includes a combustion temperature estimation value calculation unit that calculates a temperature estimation value when a mixture of fuel and inflow air is burned using an atmospheric condition, an opening degree command value of a valve that controls the amount of air that is mixed with the fuel and burned, and an output prediction value calculated on the basis of a fuel control signal command value used for calculation of a total fuel flow rate flowing through a plurality of fuel supply systems, a fuel distribution command value calculation unit that calculates a fuel distribution command value indicating a distribution of fuel output from the fuel supply systems based on the temperature estimation value, and outputs the fuel distribution command value, and a valve opening degree calculation unit that calculates each valve opening degree of a fuel flow rate control valve of the fuel supply systems.

Abstract: A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.

Abstract: Provided herein are various leptonic power sources, leptonic control systems, and leptonic-powered engines. In one example, an apparatus includes a housing having apertures through which material can enter and exit, and an anode coupled to the housing upstream from a cathode. A leptonic source emits beam electrons into the housing to ionize the material into a plasma according to a selectable ionization degree and deposit charge onto the cathode to establish an electric field in the plasma. A magnetic field source produces a magnetic field in the plasma at selectable angle to the flow of the plasma to at least partially entrain plasma electrons. Ions of the plasma are accelerated downstream in the housing by the electric field and impart momentum to a portion of the material to produce a thrust proportional to the selectable ionization degree of the plasma and a selectable intensity of the electric field.

Abstract: A heaterless hollow cathode provides electron emission current in an electric space propulsion system. A mechanical, thermal, and electromagnetic design of the cathode apparatus is presented, and a method of operation for rapid ignition and stabilization of the cathode is provided. The keeper of the cathode apparatus has a thickness change which reduces the flow of heat away from the cathode's emitter assembly. The method for heating the emitter assembly includes controlling applied voltages so that the current flowing from the emitter assembly to the keeper is maintained at a predetermined fixed value. By this method, damage to the electron emitting surfaces of the emitter assembly by electric arcing and/or by depletion of dopant materials is avoided.

Abstract: A self-pumping fuel injector includes a pump and a motor for, in-part, delivering fuel to a combustor at higher fuel pressures during start-up and ramping-up conditions. Each pump may include a stationary flow interuptor that intermittently and variably supplies fuel to a rotating spindle that, in-turn, expels the fuel into a nozzle of the injector for improve fuel spray distributions.

Abstract: A modular micro-cathode arc thruster for use in satellites. An exemplary satellite has a plurality of stacked modular arc thrusters, each having an external anode, an internal cathode, and an insulator therebetween. The arc thrusters are situated in a housing, wherein the housing has an opening to eject exhausted thrusters. Once an arc thruster is expended, the push rod ejects that arc thruster and the next arc thruster takes its place.

Abstract: A mobile fracking system and methods may include a gas turbine housed at least partially inside a trailer and an exhaust attenuation system configured to receive exhaust gas from the gas turbine. The exhaust attenuation system may include a lower elongated plenum configured to receive exhaust gas from the gas turbine and an upper noise attenuation system that is movably connected relative to a distal end of the lower elongated plenum.

Abstract: A method is provided of controlling a gas turbine having a shaft connecting a compressor to a turbine, as well as having a reheat system, and a gas turbine. The method includes the steps of: operating the engine using the reheat system to provide a mass flow rate of reheat fuel into a gas flow of the gas turbine engine downstream of an exit of the turbine; detecting a shaft break event in the shaft; and in response to this detection, maintaining the mass flow rate of the reheat fuel being provided into the gas flow downstream of the turbine exit, whereby the maintained mass flow rate of reheat fuel raises a back pressure downstream of the turbine and thereby reduces a rotational speed of the turbine.

Abstract: A nozzle tip for a premix fuel nozzle includes an outer body having an outer body external face facing the downstream end of the burner tube, the outer body external face having a smaller cross-sectional area than the cross-sectional area of the burner tube; and at least one segment radiating radially outwardly toward the internal wall of the burner tube from the outer body, wherein each segment has a proximal end disposed adjacent to the outer body external face and a distal end disposed in a direction toward the burner tube, wherein each segment has a segment downstream face angled relative to the longitudinal axis of the burner tube towards the downstream end of the burner tube. When the gas turbine is in operation, an axial flow field of an air and fuel mixture flows through the burner tube and around the nozzle tip, and two or more recirculation zones of differing radial extent are generated on the nozzle tip by the segments to provide strong flame holding and flame propagation.

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A flowpath is defined between a rotating surface and a non-rotating surface. The flowpath is connected downstream of the heat exchanger and is configured to deliver air to at least one of the plurality of rotating components. At least a portion of the non-rotating surface and the rotating surface includes a base metal. An insulation material is disposed on a surface along the flowpath.

Abstract: Provided for a device and a method for controlling a gas turbine, a gas turbine control program, and the gas turbine are: a first opening setting unit that sets a first IGV opening command value for an inlet guide vane based on factors excluding a surge limit of a compressor; a second opening setting unit that sets a second IGV opening command value for the inlet guide vane based on the surge limit of the compressor, and corrects the second IGV opening command value based on a pressure in the compressor; an opening selecting unit that selects a maximum opening as an IGV opening command value for the inlet guide vane among the first IGV opening command value and the second IGV opening command value; and an opening control unit that adjusts the opening of the inlet guide vane based on the IGV opening command value S selected by the opening selecting unit.

Abstract: A swirler for creating a swirling fuel/air mix having vanes extending radially around a central axis of the swirler and positioned on an annular base. The swirler has mixing channels for mixing the fuel and the air. At least one mixing channel is defined by opposing walls of two adjacent vanes. At least one of the opposing walls includes a primary side injection opening for ejecting a stream of fuel into the mixing channel; and a secondary side injection opening which corresponds to the primary side injection opening and is for ejecting a jet of fuel into the mixing channel. The secondary side injection opening is positioned on the wall such that the jet from the secondary side injection opening creates turbulence, within the mixing channel, in the stream from the primary side injection opening. The turbulence increases mixing of fuel and air.

Abstract: A gas turbine fuel flow rate setting device includes a flow rate ratio computing unit and a flow rate computing unit. The flow rate ratio computing unit is configured to accept a parameter having a correlation with a gas turbine output, and use a predetermined flow rate ratio relationship between the parameter and a fuel flow rate ratio between a plurality of premixing nozzle groups to determine a fuel flow rate ratio corresponding to the parameter which has been accepted. The flow rate computing unit is configured to use the fuel flow rate ratio determined by the flow rate ratio computing unit to determine a flow rate of a fuel to be supplied to each of the plurality of premixing nozzle groups.

Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, and a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow from the particulate.

Abstract: An apparatus, system and method for generating ionosonic lift is provided. First and second control electrodes are attached in a spaced-apart relation proximal to a top surface of a wing. An alternating potential applied to the first and second control electrodes alternately attracts and repels ions of a fluid in which the wing is immersed, causing a reciprocating flow of the ions of the fluid and of neutral molecules between the first and second control electrodes. The reciprocating flow of the ions and neutral molecules causes a reduction in pressure at the top surface of the wing, resulting in net lift applied to the wing under the Bernoulli relation.

Abstract: A spacecraft propulsion system comprises two thrusters, each operating in accordance to a corresponding propulsion technique. A controller is configured to direct collected solar energy to heat a propellant for consumption in one of the two thrusters, or to generate electric energy for the other one of the two thrusters.

Abstract: A mobile fracking system and methods may include a gas turbine housed at least partially inside a trailer and an exhaust attenuation system configured to receive exhaust gas from the gas turbine. The exhaust attenuation system may include a lower elongated plenum configured to receive exhaust gas from the gas turbine and an upper noise attenuation system that is movably connected relative to a distal end of the lower elongated plenum.

Abstract: A system and method for operating a combustion system comprising a fuel nozzle defining at least one main fuel circuit and at least one pilot fuel circuit is generally provided. The method includes determining an overall flow of fuel, the overall flow of fuel defining a sum total fuel through the main fuel circuit and the pilot fuel circuit; determining a plurality of ranges of ratios of main fuel flow through the main fuel circuit versus pilot fuel flow through the pilot circuit from the overall flow of fuel, wherein each range of ratios is based on a combustion criterion different from one another; determining a resultant range of ratios of main fuel flow versus pilot fuel flow based on a hierarchy of combustion criteria, wherein the hierarchy of combustion criteria provides a priority ranking of the combustion criterion; and flowing the overall flow of fuel to the main fuel circuit and the pilot fuel circuit based on the resultant range of ratios of main fuel flow versus pilot fuel flow.