An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is based on the idea of arranging a combustion chamber (10) outside a turbine (22) and providing compressed air from serially connected compressors to the combustion chamber in order to carry out a combustion process supplemented with high pressure steam pulses. The combustion chamber (10) is arranged to receive compressed air from each compressing stage of the serially connected compressors (24) for gradually increasing the amount of compressed air in the combustion chamber (10).

An aircraft power and propulsion system includes an air compressor, a heat rejection heat exchanger, a combustor positioned to receive compressed air from the air compressor as a core stream and provide thrust to the aircraft, and a closed-loop s-CO.sub.2 system. The closed-loop s-CO.sub.2 system includes carbon dioxide as a working fluid, receives power from the combustor, and rejects heat via the heat rejection heat exchanger to a cooling stream. The closed-loop system s-CO.sub.2 configured to provide power to a fan that provides the cooling stream and thrust, and power to the air compressor and at least one auxiliary load.

A method of power production using a high pressure/low pressure ratio Brayton Power cycle with predominantly N.sub.2 mixed with CO.sub.2 and H.sub.2O combustion products as the working fluid is provided. The high pressure can be in the range 80 bar to 500 bar. The pressure ratio can be in the range 1.5 to 10. The natural gas fuel can be burned in a first high pressure combustor with a near stoichiometric quantity of pressurized preheated air and the net combustion gas can be mixed with a heated high pressure recycle N.sub.2+CO.sub.2+H.sub.2O stream which moderates the mixed gas temperature to the value required for the maximum inlet temperature to a first power turbine producing shaft power.

The present disclosure relates to systems and methods useful for power production. In particular, a power production cycle utilizing CO.sub.2 as a working fluid may be combined with a second cycle wherein a compressed CO.sub.2 stream from the power production cycle can be heated and expanded to produce additional power and to provide additional heating to the power production cycle.

A system including: (i) a pumped-heat energy storage system (PHES system), wherein the PHES system is operable in a charge mode to convert electricity into stored thermal energy in a hot thermal storage (HTS) medium; (ii) an electric heater in thermal contact with the hot HTS medium, wherein the electric heater is operable to heat the hot HTS medium above a temperature achievable by transferring heat from a working fluid to a warm HTS medium in a thermodynamic cycle.

A device for generating energy from compressed air, having an air turbine for expanding gaseous air starting out from a first pressure level to a second pressure level and in the process produce first energy, a combustion chamber for receiving the air expanded in the air turbine and combust fuel in the same, and an exhaust gas turbine for expanding exhaust gas generated during the combustion of the fuel in the combustion chamber and in the process produce second energy. At least the air turbine and the exhaust gas turbine have a common housing.

An aircraft propulsion system includes a core engine, a first bottoming cycle and a second bottoming cycle that utilize different working fluids having different critical temperatures such that each of the bottoming cycles have different heat absorption capabilities.

A system includes a top cycle and a bottoming cycle. The top cycle is an engine having a combustor. The combustor receives a fuel. The combustor is capable of igniting a mix of fuel and a gas, and creating products of combustion. Products of the combustion pass downstream through a first heat exchanger. The bottoming cycle has a bottoming cycle working fluid receiving a first amount of heat through the first heat exchanger. The bottoming cycle produces work from the first amount of heat. The bottoming cycle working fluid then passes through a second heat exchanger and rejects a second lesser amount of heat. A source housing fuel is delivered to the combustor via the second heat exchanger. The bottoming cycle working fluid provides heat to the fuel being delivered to the combustor. The source is configured to maintain the fuel at a temperature equal to or below 0 F.