A method and system for bleed flow power generation is provided. The engine includes a core flowpath formed by a compressor section, a heat addition system, and an expansion section in serial flow arrangement. A bleed circuit is extended from the core flowpath to extract a portion of compressed fluid from the core flowpath. The method and system include bleeding compressed fluid through a bleed circuit extended in fluid communication from the core flowpath of the engine; flowing the compressed fluid through the bleed circuit to a turbine rotor positioned at the bleed circuit; extracting, via the turbine rotor, energy from the flow of compressed fluid across the turbine rotor; and receiving energy at an electric machine operably coupled to the turbine rotor.

Systems and methods are described herein for monitoring gas pressure within an electrolysis system and maintaining gas pressure using an electric generator to capture kinetic energy of compressed hydrogen and/or oxygen gases as they are produced by an electrolyzer. The generator utilizes a rotating apparatus, such as a fan or turbine, to capture the energy of the gases and generate electricity. Any electricity produced by the generator is fed back to the electrolyzer to supplement its energy requirements.

An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.

The present disclosure describes methods and systems for generating electricity. A method of generating electricity can include evaporating water with a low grade heat source to form low-temperature steam. The low-temperature steam can be superheated to a superheated temperature by transferring heat to the low-temperature steam from a thermal energy storage that is at a temperature higher than the superheated temperature. A steam turbine generator can be powered with the superheated steam to generate electricity. The thermal energy storage can be recharged using electricity from an intermittent electricity source.

A system includes a gas turbine engine of an aircraft, the gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool and a high spool motor configured to augment rotational power of the high speed spool. The system further includes a controller configured to cause fuel flow. The controller is configured to control a thrust response of the gas turbine engine to a thrust target between zero and a thrust level to move the aircraft during engine start and during engine idle. The controller is also configured to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.

In an embodiment, a method of modifying an existing gas turbine to create a storage engine is provided. The gas turbine has a combustor, a compressor section, and a turbine section. The method comprises the step of modifying the compressor section of the gas turbine to form the storage engine. Air supplied to the combustor of the storage engine is heated by exhaust of the storage engine and is supplied from a remote source of air. Modifying the compressor section includes removing at least some of a plurality of rotatable airfoils of a compressor of the compressor section and introducing an increased capacity thrust bearing on a shaft line.

A method of processing a stream of compressed air travelling between a gas compressor/expander subsystem and an underground accumulator in a compressed air energy storage system may include directing a thermal storage liquid through the first liquid flow path in a liquid charging flow direction from a thermal source reservoir toward a thermal storage reservoir whereby at least a portion of the thermal energy in the compressed air is transferred from the compressed air into the thermal storage liquid within the first reversible heat exchanger; including redirecting the compressed air through the first gas flow path in a gas discharging flow direction that is opposite the gas charging flow direction and redirecting the thermal storage liquid through the first liquid flow path in a liquid discharging flow direction whereby at least a portion of the thermal energy in the thermal storage liquid is returned into the compressed air.

The invention relates to a system and a method for storing electrical energy which are based on a closed thermodynamic cycle. They make it possible to store electrical energy in a very efficient, cost-effective, and safe manner. No environmentally hazardous or expensive materials are required. The system comprises a compressor, a turbine, and two packed-bed storage units which are operated at different temperature levels. In order to load the packed-bed storage units, the cycle is operated as a counterclockwise heat pump process. In this process, the heat generated at the outlet of the compressor is expanded at a high temperature level into a first packed-bed storage unit and stored therein. The “cold” produced during the subsequent expansion of the gaseous working medium in a turbine is stored in a second packed-bed storage unit. This requires mechanical energy which is provided by an electrical machine. In order to discharge the energy storage system, the cycle is operated in reverse (i.e., as a clockwise cycle). Before entering the compressor, the working medium is cooled with the cold stored in the second packed-bed storage unit and, after compression, absorbs the heat from the high-temperature packed-bed storage system. The hot working medium at high pressure is expanded by means of the turbine and thus energy is generated.

A thermal storage subsystem may include at least a first storage reservoir configured to contain a thermal storage liquid at a storage pressure that is greater than atmospheric pressure. A liquid passage may have an inlet connectable to a thermal storage liquid source and configured to convey the thermal storage liquid to the liquid reservoir. A first heat exchanger may be provided in the liquid inlet passage and may be in fluid communication between the first compression stage and the accumulator, whereby thermal energy can be transferred from a compressed gas stream exiting a gas compressor/expander subsystem to the thermal storage liquid.

An electronically speed controlled pulsed supersonic turbine engine powering automotive, drone and electric power generation, energised by breathable, clean renewable energy airflow from 2700 psi integral air-tank energising the engine continuously for 3 hours, replacing the toxic fossil gasoline-diesel energised internal combustion engine with carbon emissions that affects climate change. The turbine blades are turning by pulsed impulse of supersonic airflow from sequentially energised eight manifolds of de Laval convergence-divergence-CD with sonic choking nozzle and supersonic divergence airflow impulsing turbine blades turning them within divergence shroud to atmospheric pressure with turbine nose with engine output shaft supported with bearings supported by the air-tank. An electric pulse generator controls engine shaft speed with voltage pulses to solenoid valves commanding spool valves with airflow from the air-tank with output shaft magnetic speed sensing signal sent back to controller in closed loop adjusting to desired set with pulse amplitude and time duration.