Advanced integrated propulsion system with total optimized cycle for gas turbines

Claim 1

A gas turbine assembly with integrated high and low pressure circuits comprising: a low pressure air compressor and a high pressure air compressor staged with the low pressure air compressor; a first high pressure combustion chamber and associated two-stage, high pressure turbine communicating with the high pressure combustion chamber, the two-stage high pressure turbine having a first stage coupled to the high pressure air compressor and a second stage coupled to the low pressure air compressor; a second low pressure combustion chamber and associated low pressure, power turbine being staged with the high pressure turbine to receive combustion gases expended from the high pressure turbine; diverting means between the low pressure compressor and the high pressure compressor for diverting compressed air from the low pressure compressor to the low pressure combustion chamber; a converging chamber between the low pressure combustion chamber and the low pressure, power turbine constructed to receive and combine combustion gases from the low pressure combustion chamber and exhaust gases from the high pressure turbine; a junction valve between the low pressure combustion chamber and the covering chamber, the valve being regulatable according to power and efficiency requirements of the turbine assembly to vary the flow of compressed air from the low pressure compressor to the low pressure combustion chamber; transmission means for extracting mechanical output power, wherein the transmission means for extracting mechanical power is connected to the low pressure power turbine and the high pressure turbine drives the compressors; and, fuel supply means for supplying fuel to said first and second combustion chambers wherein a fuel and compressed air mixture is combusted and passed through said turbines.