The invention relates to a turbine engine device of the gas turbine cycle type with cooled compression, regeneration, and reheating during expansion. The turbine engine device comprises a first turbocharger (C1, T2), a second turbocharger (C2, T1), two combustion chambers (CC1, CC2), an intercooler (IC), and a heat exchanger (E1). The device is configured to implement a fluid flow from the first compressor (C1) to the intercooler (IC), to the second compressor (C2), to the heat exchanger (E1), to the first combustion chamber (CC1), to the second turbine (T1) or the first turbine, to the second combustion chamber (CC2), to the first turbine (T2) or the second turbine, According to one aspect, the turbochargers are mounted on separate axes (A1, A2).

The invention relates to a turbine engine device of the gas turbine cycle type with cooled compression, regeneration, and reheating during expansion. The turbine engine device comprises a first turbocharger (C1, T2), a second turbocharger (C2, T1), two combustion chambers (CC1, CC2), an intercooler (IC), and a heat exchanger (E1). The device is configured to implement a fluid flow from the first compressor (C1) to the intercooler (IC), to the second compressor (C2), to the heat exchanger (E1), to the first combustion chamber (CC1), to the second turbine (T1) or the first turbine, to the second combustion chamber (CC2), to the first turbine (T2) or the second turbine, According to one aspect, the turbochargers are mounted on separate axes (A1, A2).

A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

An open cycle gas turbine system includes a storage tank, a closed helical supplier, a combustor, a gas turbine, a compressor, a propeller and a generator. After the combustion gas in the combustor enters the gas turbine, the combustion gas is expanded to apply a work and to produce a power to the gas turbine so as to operate the gas turbine so that the compressor is operated to compress the air, the generator is operated to generate an electric power, and the propeller is operated to propel vehicles. The closed helical supplier has a closely sealing effect so that the high pressure combustion gas in the combustor will not leak from the closed helical supplier and will not touch the solid fuel powder in the storage tank.

An open cycle gas turbine system includes a storage tank, a closed helical supplier, a combustor, a gas turbine, a compressor, a propeller and a generator. After the combustion gas in the combustor enters the gas turbine, the combustion gas is expanded to apply a work and to produce a power to the gas turbine so as to operate the gas turbine so that the compressor is operated to compress the air, the generator is operated to generate an electric power, and the propeller is operated to propel vehicles. The closed helical supplier has a closely sealing effect so that the high pressure combustion gas in the combustor will not leak from the closed helical supplier and will not touch the solid fuel powder in the storage tank.

The closed-loop gas turbine generator is a combustion-based gas reactor for producing usable power to drive external loads. A combustion chamber produces combustion products for driving a first gas turbine, which may be connected to an external load. Exhaust from the first gas turbine is fed to an oxygen transport reactor, which produces carbon dioxide and water as output products. The carbon dioxide and water drive a second gas turbine, which may also be connected to an external load. The first gas turbine drives a compressor, which produces compressed air. Heat exchange between the compressed air and exhaust from the second gas turbine produces a stream of heated air, which is fed back to the combustion chamber in a closed-loop cycle.

The closed-loop gas turbine generator is a combustion-based gas reactor for producing usable power to drive external loads. A combustion chamber produces combustion products for driving a first gas turbine, which may be connected to an external load. Exhaust from the first gas turbine is fed to an oxygen transport reactor, which produces carbon dioxide and water as output products. The carbon dioxide and water drive a second gas turbine, which may also be connected to an external load. The first gas turbine drives a compressor, which produces compressed air. Heat exchange between the compressed air and exhaust from the second gas turbine produces a stream of heated air, which is fed back to the combustion chamber in a closed-loop cycle.

A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.