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 flow distributor changes a ratio between a flow rate of a working fluid flowing from an inlet to a first outlet and a flow rate of the working fluid flowing from the inlet to a second outlet. Into the inlet, the working fluid that is boosted by a first compressor and that is extracted from a gas turbine apparatus flows. A second compressor compresses the working fluid flowing from the first outlet. A first cooler cools the working fluid discharged from the second compressor. The first cooler cools the working fluid flowing from the second outlet to bypass the second compressor. A second expansion turbine expands the working fluid flowing from the first cooler.

The present disclosure provides systems and methods for power production. In particular, the systems and methods utilize the addition of heat to an expanded turbine exhaust stream in order to increase the available quantity of heat for recuperation and use therein for heating a compressed carbon dioxide stream for recycle back to a combustor of the power production system and method.

An aircraft propulsion system includes a core engine assembly that generates an exhaust gas flow, a bottoming cycle that includes a bottoming fluid flow that is expanded through a bottoming turbine, a first heat exchanger where heat from the exhaust gas flow is transferred to heat the bottoming fluid flow, and a second heat exchanger where heat from a secondary heat source is transferred to heat the bottoming fluid flow. The second heat exchanger is disposed upstream of the first heat exchanger such that heat from the secondary heat source preheats the bottoming fluid flow prior to accepting heat from the exhaust gas flow in the first heat exchanger.

A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.

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.

A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.

A method for operating a closed loop regenerative thermodynamic power generation cycle system is presented. The method includes supplying a high-temperature working fluid stream at a first pressure P.sub.1 to an expander, and extracting a partially expanded high temperature working fluid stream from the expander at a second pressure P.sub.2. Each of the first pressure P.sub.1 and the second pressure P.sub.2, are higher than a critical pressure of the working fluid; and the second pressure P.sub.2 is lower than P.sub.1. The method further includes regeneratively supplying the extracted high temperature working fluid stream at the second pressure P.sub.2 to a low temperature working fluid stream at the first pressure P.sub.1. A closed loop regenerative thermodynamic power generation cycle system is also presented.

The present disclosure relates to a novel gas turbine having applications, for example, in thermal power generation in an environmentally friendly manner. In various embodiments, the present disclosure provides a multiloop gas turbine with enhanced efficiency close to Ericsson/Carnot Cycle and a method of operating the multiloop gas turbine.

A facility for generating mechanical energy by means of a combined power cycle is disclosed herein, which includes at least means for carrying out a closed or semi-closed, constituent regenerative Brayton cycle, which uses water as a heat-transfer fluid, means for carrying out at least one Rankine cycle, a constituent fundamental Rankine cycle, interconnected with the regenerative Brayton cycle, and a heat pump (UAX) including a closed circuit that regenerates the constituent regenerative Brayton cycle, as well as to the method for generating energy using the facility.