Abstract: Systems and methods are provided for a digital beamformed phased array feed. The system may include a radome configured to allow electromagnetic waves to propagate; a multi-band software defined antenna array tile; a power and clock management subsystem configured to manage power and time of operation; a thermal management subsystem configured to dissipate heat generated by the multi-band software defined antenna array tile; and an enclosure assembly. The multi-band software defined antenna array tile may include a plurality of coupled dipole array antenna elements; a plurality of frequency converters; and a plurality of digital beamformers.

Abstract: Provided herein are methods, systems, and compositions for determining a base in a polynucleotide. In various aspects, the methods, systems, and compositions presented herein are useful for performing 4-base, 5-base, or 6-base sequencing of polynucleotide molecules, for example, from liquid biopsy samples or wherein the base is a low frequency mutation.

Abstract: A fuel injector to reduce NOx emissions in a combustor system. The fuel injector including a housing, at least one oxidizer flow path, extending axially through the fuel injector housing and defining therein one or more oxidizer flow paths for an oxidizer stream and a fuel manifold, extending axially through the fuel injector housing and defining therein one or more fuel flow path. The fuel manifold includes a forward portion and an aft portion including an aft face. A plurality of fuel injector outlets are defined in the aft portion, wherein the plurality of fuel injector outlets are configured to inject a fuel flow along a mid-plane of the fuel injector and away from a downstream wall. The fuel flow exiting the fuel manifold undergoes circumferential and radial mixing upon interaction with the oxidizer stream. Additionally disclosed is a combustor system including the fuel injector.

Abstract: An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.

Abstract: An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.

Abstract: Various methods and systems are provided for an engine with an exhaust gas treatment system. In one example, under a first condition, a first fuel is delivered for combustion in the engine. Under a second condition, a second fuel is delivered for combustion in the engine, the second fuel different than the first fuel. Under a third condition, the first fuel is delivered as a reductant for the exhaust gas treatment system.

Abstract: An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.

Abstract: A fuel nozzle for a gas turbine includes a first radial swirler and a second radial swirler that introduce radial swirl to a flow of pressurized air; a chevron splitter between the two swirlers that directs the swirled flow of pressurized air to a main mixer passage to form a fuel-air mixture with fuel injected into the fuel nozzle; and a main mixer passage that receives the fuel-air mixture from the premixing chamber, and includes a converging throat that accelerates the fuel-air mixture. A method of mixing fuel and air for combustion in a gas turbine includes introducing a radial swirl to first and second flows of pressurized air; directing the swirled, pressurized air to a premixing chamber via a chevron splitter; mixing the swirled, pressurized air with a fuel jet injected into the premixing chamber to form a fuel-air mixture; and accelerating the fuel-air mixture in the main mixer passage having a converging throat.

Abstract: A corrugated cyclone mixer for use in a fuel injection assembly of a turbine engine. The corrugated cyclone mixer generally includes an annular housing including a flange portion and a lip portion configured downstream of the flange portion. The mixer further including a swirler disposed therein the annular housing for inducing a cyclonic motion in the corrugated cyclone mixer. The swirler is configured upstream of the flange portion and including a plurality of swirler vanes to produce a swirling air flow. The lip portion forming an outlet downstream of the swirler and including a plurality of corrugations at an aft end. The plurality of corrugations are configured to mix the swirling air flow and an injected fuel stream flowing therethrough the corrugated cyclone mixer. Additionally disclosed is a fuel injection assembly and a turbine assembly including the corrugated cyclone mixer.

Abstract: A fuel injector to reduce NOx emissions in a combustor system. The fuel injector including a housing, at least one oxidizer flow path, extending axially through the fuel injector housing and defining therein one or more oxidizer flow paths for an oxidizer stream and a fuel manifold, extending axially through the fuel injector housing and defining therein one or more fuel flow path. The fuel manifold includes a forward portion and an aft portion including an aft face. A plurality of fuel injector outlets are defined in the aft portion, wherein the plurality of fuel injector outlets are configured to inject a fuel flow along a mid-plane of the fuel injector and away from a downstream wall. The fuel flow exiting the fuel manifold undergoes circumferential and radial mixing upon interaction with the oxidizer stream. Additionally disclosed is a combustor system including the fuel injector.

Abstract: A method of operating an engine comprises introducing into a cylinder volume a non-compression-combustible fuel, such as natural gas, a compression-combustible fuel, such as diesel, and an oxidant and mixing the components for greater than about 275 microseconds, prior to compression combusting the compression-combustible fuel. The mixing may be done such that the two fuels are at least partially homogenized in the cylinder volume. By mixing, or premixing, the two fuels prior to combustion, the compression-combustible fuel is then simultaneously combusted via compression at multiple ignition points in the volume. The second, non-compression-combustible fuel is ignited in response to the combustion of the first fuel. An engine that enables the various methods is also disclosed.

Abstract: A method of operating an engine comprises introducing into a cylinder volume a non-compression-combustible fuel, such as natural gas, a compression-combustible fuel, such as diesel, and an oxidant and mixing the components for greater than about 275 microseconds, prior to compression combusting the compression-combustible fuel. The mixing may be done such that the two fuels are at least partially homogenized in the cylinder volume. By mixing, or premixing, the two fuels prior to combustion, the compression-combustible fuel is then simultaneously combusted via compression at multiple ignition points in the volume. The second, non-compression-combustible fuel is ignited in response to the combustion of the first fuel. An engine that enables the various methods is also disclosed.

Abstract: Various methods and systems are provided for an engine with an exhaust gas treatment system. In one example, under a first condition, a first fuel is delivered for combustion in the engine. Under a second condition, a second fuel is delivered for combustion in the engine, the second fuel different than the first fuel. Under a third condition, the first fuel is delivered as a reductant for the exhaust gas treatment system.

Abstract: A turbine airfoil includes pressure and suction sidewalls extending axially in chord between opposite leading and trailing edges. The sidewalls are spaced transversely apart to define flow channels extending longitudinally and separated chordally by partitions bridging the sidewalls. A perforate partition includes a row of crossover holes extending obliquely therethrough.

Abstract: A turbine airfoil includes pressure and suction sidewalls extending axially in chord between opposite leading and trailing edges. The sidewalls are spaced transversely apart to define flow channels extending longitudinally and separated chordally by partitions bridging the sidewalls. A perforate partition includes a row of crossover holes extending obliquely therethrough.

Abstract: The present invention relates to airfoils, and in particular turbine blades and vanes, having cooling slots that are angled from a line of reference to effect metering of cooling air through the cooling slots thereof. This metered cooling airflow also creates a more stable film cooling layer about the surface of the airfoil.

Abstract: The present invention relates to a method for preventing backflow and forming a cooling layer in an airfoil by creating separation regions at a cooling slot inlet and flowing cooling fluid through the cooling slot.