The invention relates generally to methods and apparatus for integration of renewable and conventional energy to enhance electric reliability and reduce fuel consumption and emissions via thermal energy storage.

Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.

Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.

A system and method that uses one or more jet engines to remove unmanned aircraft from restricted airspace. Generally, the force created by a jet engine can be used to remove drones or other unwanted objects from the restricted airspace. Once the system determines the presence of an unauthorized aircraft or object within the restricted airspace, the jet engine(s) can be activated and used to pull the drone or flying object towards the jet engine though the force created by the intake of the jet engine(s), or to expel the drone or object from the restricted area through the force created by the exhaust of the jet engine(s).

A system and method that uses one or more jet engines to remove unmanned aircraft from restricted airspace. Generally, the force created by a jet engine can be used to remove drones or other unwanted objects from the restricted airspace. Once the system determines the presence of an unauthorized aircraft or object within the restricted airspace, the jet engine(s) can be activated and used to pull the drone or flying object towards the jet engine though the force created by the intake of the jet engine(s), or to expel the drone or object from the restricted area through the force created by the exhaust of the jet engine(s).

An exhaust energy recovery system (EERS) and associated methods for an engine are disclosed. An embodiment of an EERS, for example, includes an inlet duct that is configured to divert exhaust gas from an exhaust duct of the engine into the recovery system and an outlet duct configured to return the exhaust gas to the exhaust duct downstream of the inlet duct. The recovery system is configured to heat components or fluids associated with engine to operating temperatures. The recovery system may be part of a mobile power system that is mounted to a single trailer and includes an engine and a power unit such as a high pressure pump or generator mounted to the trailer. Methods of operating and purging recovery systems are also disclosed.

A combined power plant is provided. The combined power plant includes a gas turbine configured to combust fuel to generate a rotating force, a boiler configured to heat water to generate steam, an ammonia decomposition apparatus configured to receive a combustion gas generated in the gas turbine to thermally decompose ammonia to generate a decomposed gas containing hydrogen, nitrogen, and a residual ammonia, a steam turbine configured to generate a rotating force using the steam generated in the boiler, and a decomposed gas supply line configured to supply the decomposed gas generated in the ammonia decomposition apparatus to a combustor of the gas turbine.

A combined circulating system of a micro gas turbine, a transportation means, and a charging system are provided. The circulating system includes the micro gas turbine, a heat exchange unit, a circulating water tank, a piston engine, and a power generating apparatus, wherein the micro gas turbine is provided with a regenerator; an exhaust port of the regenerator is connected with an air inlet of the heat exchange unit to provide a heat source to the heat exchange unit; the exhaust port of the heat exchange unit is led to atmosphere, a water inlet of the heat exchange unit is connected with a water outlet of the circulating water tank, and a steam outlet of the heat exchange unit is connected with the piston engine to enable high pressure steam to enter the piston engine to push the piston engine to produce work.

The present invention provides a direct-fired supercritical carbon dioxide power generation system and a power generation method thereof, the system comprising: a combustor for burning hydrocarbon fuel and oxygen; a turbine driven by combustion gas discharged from the combustor; a heat exchanger for cooling combustion gas discharged after driving the turbine, by heat exchange with combustion gas recycled and supplied to the combustor; and an air separation unit for separating air to produce oxygen, wherein a portion of the combustion gas discharged after driving the turbine is branched before being introduced to the heat exchanger and is supplied to the air separation unit.

An aircraft installation of a pneumatic system of an aircraft with different compressed air sources for supplying pressurized air to air consumer equipment. Either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition, for instance the flight altitude or specific flight phases. Also, a turbofan engine, and a method for supplying compressed air to air consumer equipment are disclosed.