A process is provided for recycling Hydrogen enrichment tail gas to a combined cycle power system.

A power plant comprises a combustor for combusting first and second constituents to generate a gas stream, a turbine for rotation by the gas stream, a compressor to receive a first portion of the gas stream and provide compressed gas to the combustor, a recompressor configured to receive a second portion of the gas stream and provide compressed gas to the combustor, a generator to be driven by the turbine, and a methane reforming reactor configured to dry reform methane to provide the first constituent. A method of operating a power plant comprises operating a supercritical CO2 power cycle to turn a turbine, driving a generator with the turbine, extracting CO2 byproduct from the power cycle, reacting fuel and CO2 to produce a synthesis gas in a dry reforming of methane reactor, and mixing the synthesis gas with oxygen to execute a combustion process for the power cycle.

A processing facility is provided. The processing facility includes an asphaltenes and metals (AM) removal system configured to process a feed stream to produce a power generation stream, a hydroprocessing feed stream, and an asphaltenes stream. A power generation system is fed by the power generation feed stream. A hydroprocessing system is configured to process the hydroprocessing feed stream to form a gas stream and a liquid stream. A hydrogen production system is configured to produce hydrogen, carbon monoxide and carbon dioxide from the gas feed stream. A carbon dioxide conversion system is configured to produce synthetic hydrocarbons from the carbon dioxide, and a cracking system is configured to process the liquid feed stream.

A processing facility is provided. The processing facility includes an asphaltenes and metals (AM) removal system configured to process a feed stream to produce a power generation stream, a hydroprocessing feed stream, and an asphaltenes stream. A power generation system is fed by the power generation feed stream. A hydroprocessing system is configured to process the hydroprocessing feed stream to form a gas stream and a liquid stream. A hydrogen production system is configured to produce hydrogen, carbon monoxide and carbon dioxide from the gas feed stream. A carbon dioxide conversion system is configured to produce synthetic hydrocarbons from the carbon dioxide, and a cracking system is configured to process the liquid feed stream.

A powerplant is provided that includes a pre-burner, a combustor, a power turbine, a mechanical load and a propellant system. The combustor is fluidly coupled with and downstream of the pre-burner. The power turbine is fluidly coupled with and downstream of the combustor. The mechanical load is rotatably driven by the power turbine. The propellant system is configured to direct fluid oxygen and fluid hydrogen to the pre-burner to provide an oxygen rich fuel mixture for combustion within the pre-burner. The propellant system is also configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within combustion products received from the pre-burner.

Disclosed herein is a fuel for use in a combustor of a gas turbine, wherein the fuel is a gas mixture that comprises hydrogen and exhaust gas from a total combustor.

A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.

A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.

Oxy-fuel combustion of a fuel stream, an oxygen stream and a recycle stream can form an exhaust stream, with, for example, a gas turbine. The exhaust stream can be separated into a water-rich stream and a carbon dioxide-rich stream. At least a portion of the carbon dioxide-rich stream can be divided to form the recycle stream. A second portion of the carbon dioxide-rich stream and a hydrogen stream can generate an exit stream, with, for example, a Sabatier reactor. The exit stream can be separated into a methane-rich gaseous product and a water-rich liquid product.

Oxy-fuel combustion of a fuel stream, an oxygen stream and a recycle stream can form an exhaust stream, with, for example, a gas turbine. The exhaust stream can be separated into a water-rich stream and a carbon dioxide-rich stream. At least a portion of the carbon dioxide-rich stream can be divided to form the recycle stream. A second portion of the carbon dioxide-rich stream and a hydrogen stream can generate an exit stream, with, for example, a Sabatier reactor. The exit stream can be separated into a methane-rich gaseous product and a water-rich liquid product.