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 combustor of an embodiment includes: a cylindrical combustor liner; and a fuel nozzle which is provided at one end of the combustor liner and jets a fuel and an oxidant into the combustor liner. The fuel nozzle includes: a plurality of fuel supply passages which each supply the fuel; and a plurality of oxidant supply passages which each supply the oxidant. Flow rates of the fuel supplied to the respective fuel supply passages and flow rates of the oxidant supplied to the respective oxidant supply passages are each individually regulated.

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 method for energy conversion from pressure energy into electrical energy uses an expansion turbine. In the method, a pressurized, gaseous, first medium is heated before being fed into the expansion turbine. The expansion turbine drives a generator and a compressor. At least one gaseous second medium is compressed by the compressor in a heating arrangement. Heat generated by the compression and preferably also via utilization of ambient heat according to a heat exchanger principle is used for heating the gaseous first medium.

A control method of a centrifugal compressor (C) mechanically coupled to an expansion turbine (TorC), the centrifugal compressor (C) being provided with at least a control system (20) of the absorbed power. The control method of the rotation speed of the turbine-centrifugal compressor group performs the following steps: acting on the centrifugal compressor control system (20) of the absorbed power by means of a first controller (PID-f), in order to keep constant the rotational speed of the compressor mechanically coupled to the expansion turbine;ensuring that the centrifugal compressor (C) remains in a stable operating condition by means of an admission valve (Vi) of the expansion turbine (TorC).

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.

The present disclosure relates to a power generation system and related methods that use supercritical fluids, whereby a portion of the supercritical fluid is recuperated.

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).

A fluid flow turbine having a turbine rotor with a plurality of blades (also known as vanes) for converting the kinetic energy of a flowing fluid into mechanical rotational energy of the turbine rotor is provided by this invention. The plurality of blades are defined by a continuously sinuous curve outer edge that results in the lateral surface of the blades having a lower concave portion for scooping up the horizontal incoming fluid flow and redirecting it to a substantially vertical fluid flow along the lateral surface of the blade. The upper portion of the lateral surfaces of the blades is convex, causing the upper edge of the blades to tail off laterally so that the fluid flow exits the turbine in a substantially vertical direction, instead of turning back upon itself to reduces turbulence of the fluid flow inside the turbine. The fluid flow turbine can comprise a small wind turbine that will produce electrical power at low wind speeds, and can be mounted to the top of a building.

A gas turbine engine may include a deep heat recovery system, such as a deep heat recovery super critical carbon dioxide (sCO2) system. The deep heat recovery system may include two-stage cooling of the working fluid (such as carbon dioxideCO2) where at least one of cooling stages is recuperative by transferring heat from the working fluid to a flow of compressed air being supplied to a combustor included in the gas turbine engine. The deep heat recovery system may operate in a supercritical cycle, or in a transcritical cycle depending on the temperature to which the working fluid is cooled during a second stage of the two-stage cooling. The second stage of the two-stage cooling includes working fluid-to-air heat rejection where the air is ambient air.