A system and a method for driving a fan of an engine of an aircraft, including an electric motor operatively coupled to a drive axle of the fan, and a control unit in communication with the electric motor. The control unit is configured to operate the electric motor to rotate the fan.

A system and a method for driving a fan of an engine of an aircraft, including an electric motor operatively coupled to a drive axle of the fan, and a control unit in communication with the electric motor. The control unit is configured to operate the electric motor to rotate the fan.

A system includes a generator using a fluid mixture obtained via a generator inlet, a compressor having a compressor inlet that is connected to a generator outlet by a first set of conduits, a second set of conduits connected to the compressor outlet and the generator inlet, and a sensor in communication with the second set of conduits, where a portion of the fluid mixture includes gas from a hydrocarbon well, and where exhaust fluid of the generator is provided to the compressor. A process includes obtaining a target fluid property and a fluid measurement using the sensor and modifying a parameter of a fluid control device to modify a first flow rate of the flow of the exhaust fluid through the second set of conduits relative to a second flow rate of the flow of the gas provided by the hydrocarbon well through the first set of conduits.

Shape memory alloy (SMA) actuators and thermal management systems including the same. An SMA actuator includes an SMA lifting tube and a process fluid conduit configured to convey a process fluid through the SMA lifting tube. The SMA actuator assumes a conformation that is based on the temperature of the process fluid. The SMA lifting tube includes a first end and a second end configured to translate relative to the first end at least partially along a lateral direction. A thermal management system is configured to regulate a temperature of a process fluid. The thermal management system includes a heat exchanger that at least partially defines a heat transfer region, a process fluid conduit configured to convey the process fluid through the heat transfer region, and an actuator assembly including the SMA actuator. The actuator assembly is configured to selectively position the heat exchanger within a thermal management fluid flow.

A system includes an inlet duct disposed about an inlet axis, wherein the inlet duct is configured to direct an airflow along the inlet axis to a compressor inlet. The inlet includes an inlet heating system and a heating portion having a longitudinal axis that is substantially perpendicular to the inlet axis. The inlet heating system includes a first conduit substantially parallel to the longitudinal axis that is configured to distribute a heated fluid directly to the airflow via a first set of openings of a first end zone of the first conduit and a second set of openings of a second zone of the first conduit. The first end zone is configured to receive the heated fluid from a heating source, the second zone is coupled to the first end zone, and the second zone is configured to receive the heated fluid from the first end zone.

An integrated ITM micromixer burner shell and tube design for clean combustion in gas turbines includes an oxy-fuel micromixer burner for separating oxygen from air within the burner to perform oxy-combustion, resulting in an exhaust stream that consists of CO.sub.2 and H.sub.2O. The shell and tube combustion chamber is designed so that preheated air enters a headend having an array of ion transfer membrane (ITM) tubes that separate oxygen from the preheated air and anchor flamelets on the shell side. The combustion products of the oxy-fuel flamelets expand through a turbine for power generation, before H.sub.2O is separated from CO.sub.2 by condensation. A portion of the effluent CO.sub.2 is compressed back into the burner system, while the remainder is captured for sequestration/utilization.

An auxiliary propulsion apparatus of an air vehicle may include an engine mounted in a fuselage of the air vehicle, a generator configured to be driven using power from the engine, a compressor configured to be driven by the engine or the generator, a battery configured to store electricity generated by the generator, an electricity distributor connected to the generator, the battery and the main propulsion apparatus and configured to distribute electricity generated by the generator to the battery and to a main propulsion apparatus, and at least one nozzle device configured to jet high-pressure gas, supplied from the compressor, to an outside of the fuselage.

Systems and methods for variable pressure inventory control of a closed thermodynamic cycle power generation system or energy storage system, such as a reversible Brayton cycle system, with at least a high pressure tank and an intermediate pressure tank are disclosed. Operational parameters of the system such as working fluid pressure, turbine torque, turbine RPM, generator torque, generator RPM, and current, voltage, phase, frequency, and/or quantity of electrical power generated and/or distributed by the generator may be the basis for controlling a quantity of working fluid that circulates through a closed cycle fluid path of the system.

Systems and methods for variable pressure inventory control of a closed thermodynamic cycle power generation system or energy storage system, such as a reversible Brayton cycle system, with at least a high pressure tank and an intermediate pressure tank are disclosed. Operational parameters of the system such as working fluid pressure, turbine torque, turbine RPM, generator torque, generator RPM, and current, voltage, phase, frequency, and/or quantity of electrical power generated and/or distributed by the generator may be the basis for controlling a quantity of working fluid that circulates through a closed cycle fluid path of the system.

A fluid delivery device is provided that includes a sleeve and a tube. The sleeve extends axially along an axis between a sleeve first end and a sleeve second end. The sleeve extends radially from a sleeve inner side to a sleeve outer side. The sleeve extends circumferentially around the axis thereby forming an internal bore at least partially formed by a bore surface at the sleeve inner side. The internal bore extends axially along the axis through sleeve between the sleeve first end and the sleeve second end. The tube is connected to the sleeve and projects out from the sleeve outer side to a tube distal end. The tube is configured with a delivery device fluid passage fluidly coupled with the internal bore. The delivery device fluid passage extends radially through the tube to a fluid passage outlet at the tube distal end.