Abstract: A method of manufacturing an internally cooled blisk by additive manufacturing processes to provide weight reduction and power-to-weight ratio improvement, leading to improved efficiency, a decrease in fuel burn and lifecycle costs in an engine employing the internally cooled blisk. The method of manufacturing including defining a configuration for the internally cooled blisk, the configuration comprising a disk, an annular array of angularly spaced blades extending about a periphery of the disk and one or more internal cooling features defined within the internally cooled blisk. The method further including the step of programming the configuration into an additive manufacturing system. A powder is deposited into a chamber and an energy source is applied to the deposited powder to consolidate the powder into a cross-sectional shape corresponding to the defined configuration. Additionally provided is an internally cooled blisk.

Abstract: A gas detector and method are presented. The gas detector includes a launcher unit for coupling and merging light beams in mid-infrared and infrared wavelength ranges into a single light beam and directing the merged single light beam towards a gas flow path; a receiver unit for generating at least one photo detector current signal based on the light beam transmitted through the gas flow path; and a control unit for processing at least one photo detector current signal to measure concentration of the at least two gases present in the gas flow path.

Abstract: A system includes an engine coupled with a primary shaft that drives a first electric generator for generating electrical power via a gear subsystem, The system also includes a turbocharger assembly having at least one gas turbine engine configured for driving the primary shaft and coupled in parallel with the engine. The turbocharger assembly includes multiple compressors configured to provide a flow of compressed fluid into both the engine and the at least one gas turbine engine and multiple turbines configured to utilize exhausts from both the engine and the one gas turbine for driving the primary shaft. Further, the system includes a controller configured to operate a plurality of valves for controlling optimal intake fluid pressure into the engine and the turbocharger assembly and fuel injections into the engine and the at least one gas turbine engine.

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 method of operating a gas turbine engine includes measuring an exhaust gas temperature of the gas turbine engine. A first stage turbine nozzle assembly of the gas turbine engine is adjusted to a first position. A firing temperature of the gas turbine engine is determined based on the exhaust gas temperature. The firing temperature is compared to a threshold value and a difference value is determined therefrom. If the difference value exceeds a threshold value, the first stage turbine nozzle assembly is adjusted to a second position such that the firing temperature is substantially equal to the threshold value.

Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

Abstract: A method implemented using at least one processor includes acquiring sensor data from a plurality sensors disposed on a vehicle configured to engage an aircraft for ground operation, wherein the aircraft is a member of a fleet of aircrafts. The method further includes receiving a plurality of environmental parameters from a supervisory system, wherein the supervisory system receives data from at least one of a gate, a service vehicle, a taxi vehicle, another aircraft, and a control center. The method also includes determining a plurality of contextual parameters representative of status of the vehicle based on the sensor data and the plurality of environmental parameters. The method further includes generating a plurality of control parameters based on the plurality of contextual parameters and the plurality of environmental parameters and providing at least one of the plurality of the control parameters to the vehicle for managing airport traffic.

Abstract: A turbine engine assembly is provided. The assembly includes a low-pressure turbine assembly including a first turbine section configured to rotate in a first rotational direction at a first rotational speed, and a second turbine section configured to rotate in a second rotational direction at a second rotational speed. The second rotational direction is opposite the first rotational direction and the second rotational speed is lower than the first rotational speed. The assembly also includes a first drive shaft coupled to the first turbine section, and a fan assembly including a first fan section coupled to the first drive shaft such that the first fan section rotates in the first rotational direction at the first rotational speed, and a second fan section coupled to the second turbine section such that the second fan section rotates in the second rotational direction at the second rotational speed.

Abstract: A method implemented using at least one of the processor includes disposing a power source on a vehicle, wherein the power source is configured to power auxiliary loads of the aircraft. The method also includes connecting a power source disposed on a vehicle configured to engage an aircraft for ground operation, to auxiliary loads of the aircraft via an on-board power system. The method also includes performing energy management of the aircraft during the period of ground operation. The method further includes disconnecting the power source when an alternate electrical power is available to the on-board power system.

Abstract: A method implemented using at least one processor includes receiving a plurality of images acquired from a plurality of image sensors disposed on a vehicle configured to engage an aircraft for ground operations. The method further includes determining at least one parameter about a potential obstacle based on the plurality of images and a machine vision algorithm. The method also includes generating an alert signal based on the at least one parameter, useful for avoiding collision of the aircraft.

Abstract: An inlet particle separator system coupled to an engine having an engine exhaust is presented. The inlet particle separator system includes an axial flow separator for separating air from an engine inlet into a first flow of substantially contaminated air and a second flow of substantially clean air. The inlet particle separator system further includes a scavenge subsystem in flow communication with the axial flow separator for receiving the first flow of substantially contaminated air. Furthermore, the inlet particle separator system includes a fluidic device including a first inlet and an exhaust, where the fluidic device is configured to accelerate the first flow of substantially contaminated air through the scavenge subsystem and emit the first flow of substantially contaminated air via the exhaust of the fluidic device, wherein the exhaust of the fluidic device is different from an exhaust of the engine.

Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

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 permanent magnet machine and a rotor assembly for the permanent magnet machine. The permanent magnet machine includes a stator assembly including a stator core configured to generate a magnetic field and extending along a longitudinal axis with an inner surface defining a cavity and a rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and configured to rotate about the longitudinal axis. The rotor assembly further including a plurality of permanent magnets for generating a magnetic field which interacts with the stator magnetic field to produce torque. The permanent magnets are disposed within one or more cavities formed in a sleeve component. The sleeve component configured to include a plurality of cavities or voids therein and thus provide minimal weight to the permanent magnet machine. The permanent magnet machine providing increased centrifugal load capacity, increased power density and improved electrical performance.

Abstract: Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.

Abstract: A system for premixing fuel and air prior to combustion in a gas turbine engine includes a mixing duct, a centerbody fuel injector located along a central axis of the mixing duct, an outer annular swirler located adjacent an upstream end of the mixing duct for swirling air flowing therethrough in a first swirl direction and an inner annular swirler located adjacent of the mixing duct upstream end for swirling air flowing therethrough in a second swirl direction. The system includes a hub separating said inner and outer annular swirlers to permit independent rotation of an air stream therethrough and multiple hollow paths located radially outward around the centerbody fuel injector and at a radially inward side of the inner annular swirler for allowing a flow of sweeping air over the surface of the centerbody fuel injector.

Abstract: A cooling system for a turbine engine including a heat exchanger in fluid communication with a first fluid inlet stream and disposed upstream and in fluid communication with a core engine. The heat exchanger operative to cool the first fluid inlet stream. The heat exchanger including a heat exchanger inlet for input of a heat exchanging medium for exchange of heat from the first fluid inlet stream to the heat exchanging medium. The heat exchanger further including a heat exchanger outlet for discharge of a heated output stream into one of a turbine of a downstream engine, an augmentor or a combustor of the core engine. The heated output stream provides an additional flow to the downstream engine. A turbine engine including the cooling system is disclosed.

Abstract: A tuned cavity rotating detonation combustion system includes a an annular chamber having an inlet and an outlet; a valve plate at the inlet of the annular chamber and comprising a plurality of openings spaced circumferentially around the inlet; a plurality of tubes each having an open end in communication with a corresponding opening of the valve plate and a closed end forming a tuned cavity, and a first opening between the open end and the closed end for injection of air; and a plurality of fuel injectors corresponding to the plurality of tubes, each fuel injector being configured to inject fuel into the tube between the first opening and the open end. Each of the tuned cavities has a length sized to resonate at a same frequency as a continuous detonation frequency of at least one detonation wave in the annular chamber.

Abstract: A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath.