Abstract: A gas turbine engine having an air compressor and a combustion chamber connected to the air compressor for burning fuel with air from the air compressor. The combustion chamber also has water and/or steam as input. The water and/or steam is combined with the gases generated by the burning of the fuel to generate a gaseous output that drives first and second turbines. A heat recovery system recovers heat and water from the gaseous output after the gaseous output has passed through the turbines. The water is used as the water source for the combustion chamber and for cooling the turbines. In the preferred embodiment of the present invention, the heat recovery system utilizes a supercritical heat exchanger. Some of the recovered heat is preferably utilized to drive a third expander.

Abstract: A dual cycle engine which includes both a steam turbine and a gas turbine. The engine includes an air compressor and a combustion chamber connected to the air compressor for burning fuel with air from the air compressor to generate a first gaseous output which drives a gas turbine. The engine also includes a heat recovery system for recovering heat from the gaseous output of the gas turbine after the gaseous output has passed through the gas turbine. The heat recovery system includes a heat exchanger for extracting heat from the gaseous output and for heating an input water stream to generate steam. The steam is heated further in a superheater that burns fuel and air at the same pressure as the combustion chamber to generate a second gaseous output that is combined with the output of the combustion chamber prior to the output from the combustion chamber being passed through the gas turbine. The steam from the superheater is expanded in a steam turbine to generate work therefrom.

Abstract: A dual cycle engine which includes both a steam turbine and a gas turbine. The engine includes an air compressor and a combustion chamber connected to the air compressor for burning fuel with air from the air compressor to generate a first gaseous output which drives a gas turbine. The engine also includes a heat recovery system for recovering heat from the gaseous output of the gas turbine after the gaseous output has passed through the gas turbine. The heat recovery system includes a heat exchanger for extracting heat from the gaseous output and for heating an input water stream to generate steam. The steam is heated further in a superheater that burns fuel and air at the same pressure as the combustion chamber to generate a second gaseous output that is combined with the output of the combustion chamber prior to the output from the combustion chamber being passed through the gas turbine. The steam from the superheater is expanded in a steam turbine to generate work therefrom.

Abstract: A two-stage rotating vane device comprising an outer stator defining a plurality of ports and an elliptically or cylindrically shaped interior cavity surface, with an inner stator defining a plurality of ports, the inner stator either being elliptically shaped or configured in a predetermined shape and located in the elliptically or cylindrically shaped interior cavity. A rotor is disposed in the elliptically or cylindrically shaped interior cavity between the interior cavity surface of the outer stator and the inner stator, the rotor defining a plurality of slots. A plurality of slidable vanes are situated in the plurality of slots for spanning between the interior cavity surface of the outer stator and the inner stator, and wherein a first stage is defined between the inner stator and the rotor, and a second stage is defined between the interior cavity surface of the outer stator and the rotor, the first and second stages communicating with each other.

Abstract: A gas turbine engine having an air compressor and a combustion chamber connected to the air compressor for burning fuel with air from the air compressor. The combustion chamber also has water and/or steam as input. The water and/or steam is combined with the gases generated by the burning of the fuel to generate a gaseous output that drives first and second turbines. A heat recovery system recovers heat and water from the gaseous output after the gaseous output has passed through the turbines. The water is used as the water source for the combustion chamber and for cooling the turbines. In the preferred embodiment of the present invention, the heat recovery system utilizes a supercritical heat exchanger. Some of the recovered heat is preferably utilized to drive a third expander.

Abstract: A power generating combustion system and method are provided with a first stage combustion system that may include a wet oxidation reactor or a direct contact boiler and a second stage combustor including a stoichiometric burner to produce the substantially complete combustion of a wide range of fuels and mixtures of fuels to produce combustion products usable in generating power. The system design temperatures and pressures allow the substantially complete combustion of garbage, municipal and industrial waste and low quality fuels to generate power.

Abstract: A power generating combustion system and method are provided with a first stage combustion system that may include a wet oxidation reactor or a direct contact boiler and a second stage combustor including a stoichiometric burner to produce the substantially complete combustion of a wide range of fuels and mixtures of fuels to produce combustion products usable in generating power. The system design temperatures and pressures allow the substantially complete combustion of garbage, municipal and industrial waste and low quality fuels to generate power.

Abstract: An improved thermal efficiency power plant for converting fuel energy to shaft horsepower is described. The conventional combustor of a gas tubine power plant is replaced by a direct contact steam boiler 8, modified to produce a mixture of superheated steam and combustion gases. Combustion takes place preferably at stoichiometric conditions. The maximum thermal efficiency of the disclosed plant is achievable at much higher pressures than conventional gas turbines. Uses of multi-stage compression turbines (4, 9, 1, 10) with intercooling (2, 3) and regeneration (16, 17, 18, 19) is utilized along with a vapor bottoming cycle (11, 12, 13) to achieve a thermal efficiency greater tha 60% with a maximum drive turbine inlet temperature of 1600 degrees Fahrenheit.