In a conventional screw compressor, two mating rotors which resemble screws are assembled in parallel with each other within a housing. These rotors are very costly to manufacture, and it is very difficult to extract all of the gas that has been compressed between the lobes of the rotor screws. This invention eliminates the twist of the lobes around the rotor of a conventional screw compressor. In this invention, the lobes are manufactured in line with the axis of the rotor (axially). As a result, the costs of manufacturing the rotors are reduced dramatically, and the natural tendency for the gas to be driven towards the center of the female rotor is taken advantage of, making it much easier to extract practically all of the gas that has been compressed between the lobes.

A rotor assembly for an engine, comprising: a rotor, supported on bearings for axial rotation, a rotor portion forming a compression passage extending outwards from the axis, gases entering the rotor through inlets at the axis and flowing outwards through the compression passage; a combustion chamber supported within the compression passage near the maximum radius of the rotor having a closed outer end and combustion chamber gases inlets through which gases enter the combustion chamber, each combustion chamber having a fuel inlet, and; one or more expansion passages in fluidic connection with and extending radially inwards from the combustion chamber within a compression passage and fluidically connecting at or near the rotor axis to a combustion gas outlet tube that extends along the rotor axis, combustion gases created by combustion of fuel with inlet gases within the combustion chamber expanding as they flow inwards through the expansion passage.

A rotor assembly for an engine, comprising: a rotor, supported on bearings for axial rotation, a rotor portion forming a compression passage extending outwards from the axis, gases entering the rotor through inlets at the axis and flowing outwards through the compression passage; a combustion chamber supported within the compression passage near the maximum radius of the rotor having a closed outer end and combustion chamber gases inlets through which gases enter the combustion chamber, each combustion chamber having a fuel inlet, and; one or more expansion passages in fluidic connection with and extending radially inwards from the combustion chamber within a compression passage and fluidically connecting at or near the rotor axis to a combustion gas outlet tube that extends along the rotor axis, combustion gases created by combustion of fuel with inlet gases within the combustion chamber expanding as they flow inwards through the expansion passage.

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 fluidfoil comprises a main body and a fence, wherein the fence has different lean angles with respect to the main body at different chordwise positions, and wherein the fence is divided along its chordwise extent into at least two portions, where a first portion nearer a leading edge of the fence has a smaller lean angle than a second portion further from the leading edge, and wherein all portions are either anhedral or dihedral.

A fluidfoil comprises a main body and a fence, wherein the fence has different lean angles with respect to the main body at different chordwise positions, and wherein the fence is divided along its chordwise extent into at least two portions, where a first portion nearer a leading edge of the fence has a smaller lean angle than a second portion further from the leading edge, and wherein all portions are either anhedral or dihedral.

The present invention is directed to methods and systems for utilizing supercritical carbon dioxide in an open thermodynamic cycle in which no compressors are used. In some embodiments, a method for utilizing supercritical carbon dioxide includes combusting oxygen, fuel, and heated recycled supercritical carbon dioxide to produce a gas that is fed to a turbine to generate power; using the exhaust gas from the turbine to preheat the recycled supercritical carbon dioxide that is fed to the turbine; and pass the exhaust gas through a series of two sets of condensers and separators to provide a carbon dioxide stream from which the recycled supercritical carbon dioxide is generated using a pump. Power for the pump is provided by the turbine, which also provides power to an electric generator.

The present invention is directed to methods and systems for utilizing supercritical carbon dioxide in an open thermodynamic cycle in which no compressors are used. In some embodiments, a method for utilizing supercritical carbon dioxide includes combusting oxygen, fuel, and heated recycled supercritical carbon dioxide to produce a gas that is fed to a turbine to generate power; using the exhaust gas from the turbine to preheat the recycled supercritical carbon dioxide that is fed to the turbine; and pass the exhaust gas through a series of two sets of condensers and separators to provide a carbon dioxide stream from which the recycled supercritical carbon dioxide is generated using a pump. Power for the pump is provided by the turbine, which also provides power to an electric generator.

In a power generation system, exhausted fuel gas exhausted from a solid oxide fuel cell (SOFC) is used as a fuel of a first combustor or a second combustor of a gas turbine, and at the same time, a part of compressed air compressed by a compressor of the gas turbine is used to drive the SOFC. The gas turbine includes the first combustor for burning fuel gas which is different from the exhausted fuel gas, a first turbine configured to be driven by combustion gas supplied from the first combustor, the second combustor for burning at least a part of the exhausted fuel gas, and a second turbine coupled with the first turbine and configured to be driven by combustion gas supplied from the second combustor.