A direct-fired gas turbine heater comprises a gas turbine engine, a main blower that receives cold air from the ambient, a mixing plenum that receives cold air from the main blower and hot gas from the turbine and delivers warm air, an air blower plenum that that receives cold air from the main air blower and delivers air to the mixing plenum, and an air intake plenum that receives cold air from the ambient and the air blower plenum and delivers cold air to a turbine compressor, an air intake valve, and an air starter valve. The gas turbine engine comprises the compressor that receives cold air, a fuel manifold that receives combustible fuel, a combustor that receives compressed air from the compressor and fuel from the fuel manifold, a turbine that receives hot gas from the combustor, and a shaft connecting the compressor and turbine.

A propulsion system including: a fuel cell assembly comprising a fuel cell, the fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from the aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including: delivering the output products from the fuel cell to the combustion section to mitigate combustion dynamics within the combustion section.

A gas turbine engine includes; a compressor, a combustor, and a turbine in serial flow relationship; a heat exchanger, the heat exchanger having an inlet, an outlet, and an internal surface coated with a catalyst, the heat exchanger being located upstream of the compressor; a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger; a source of oxygen in fluid communication with the inlet of the heat exchanger; and a distribution system for receiving reformed hydrocarbon fuel from the heat exchanger.

The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration.

The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration.

A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor.

A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor.

An integrated chemical looping combustion (CLC) electrical power generation system and method for diesel fuel combining four primary units including: gasification of diesel to ensure complete conversion of fuel, chemical looping combustion with supported nickel-based oxygen carrier on alumina, gas turbine-based power generation and steam turbine-based power generation is described. An external combustion and a heat recovery steam generator (HRSG) are employed to maximize the efficiency of a gas turbine generator and steam turbine generator. The integrated CLC system provides a clean and efficient diesel fueled power generation plant with high CO.sub.2 recovery.

The fuel system can have a jet fuel subsystem having a jet fuel conduit extending from a first reservoir area to a fuel nozzle across an auxiliary system operable using a flow of the jet fuel, at least one fuel delivery system operable to circulate a controlled flow rate of the jet fuel within said conduit and across the auxiliary system, a recirculation conduit branching off from the jet fuel conduit downstream of the auxiliary system, an actuator valve operable to selectively direct a flow of jet fuel to the at least one fuel nozzle or to the recirculation conduit; and an alternative fuel subsystem having an alternative fuel conduit extending from a second reservoir area to a fuel nozzle.

The method can include simultaneously conveying a controlled flow rate of jet fuel from a first reservoir area of the aircraft to a fuel nozzle across at least one auxiliary system, including the at least one auxiliary system using the controlled flow rate of jet fuel for operation and conveying a controlled flow rate of an alternative fuel from a second reservoir area of the aircraft to the fuel nozzle.