Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber.

A hybrid power generation system using solar energy and bioenergy, including a solar thermal boiler system, a biomass boiler system, and a turbogenerator system. The solar thermal boiler system includes a trough solar collector, a heat collector, an oil circulating pump, a storage tank for storing heat transfer oil, a solar thermal heater, a solar thermal evaporator, a main pipe transporting saturated steam, and an auxiliary boiler. Heat transfer oil output from a solar light field of the solar thermal boiler system is transmitted through and transfers heat to the solar thermal evaporator and the solar thermal heater, and the heat transfer oil returns to the storage tank for storing heat transfer oil. The heat transfer oil in the storage tank is pumped to the solar light field via the oil circulating pump.

A method of operating a hydrocarbon production system. The hydrocarbon production system including a gas turbine engine configured to combust hydrocarbon gas produced at the hydrocarbon production system and to provide power for the hydrocarbon production system as a result of the combustion. The method includes combusting produced hydrocarbon gas in the gas turbine engine, capturing carbon dioxide exhausted from the gas turbine engine as a result of the combustion of the hydrocarbon gas, storing the captured carbon dioxide at the hydrocarbon production system in a first set of storage pipes, and transporting the stored carbon dioxide away from the hydrocarbon production system for permanent storage.

A gas turbine engine for an aircraft, comprising: a combustor; a fuel-oil heat exchanger arranged to receive fuel from a fuel tank on board the aircraft and transfer heat from the oil to the fuel; a fuel return line arranged to return at least some fuel that has passed through the heat exchanger to the fuel tank; and a modulator valve arranged to modulate the flow of fuel along the fuel return line such that a ratio of a temperature, in Kelvin, of fuel in the fuel tank to a temperature, in Kelvin, of fuel being delivered to the combustor is less than 0.56. Methods of operating a gas turbine engine are also disclosed.

A gas turbine combustor according to at least one embodiment, includes: a less combustible fuel flow control part for controlling, independently of each other, amounts of less combustible fuel supplied to a first fuel injector and a second fuel injector; a highly combustible fuel flow control part for controlling, independently of each other, amounts of highly combustible fuel having a higher combustion speed than the less combustible fuel and supplied to the first fuel injector and the second fuel injector; and a controller configured to control the less combustible fuel flow control part and the highly combustible fuel flow control part such that a relative ratio of a first ratio of the highly combustible fuel to whole of first fuel injected by the first fuel injector and a second ratio of the highly combustible fuel to whole of second fuel injected by the second fuel injector changes according to an operating condition of a gas turbine.

A fuel conditioning system configured to supply a turbomachine with fuel from a cryogenic tank, the conditioning system comprising a fuel circuit connected at the inlet to the cryogenic tank and at the outlet to the turbomachine, a pump, a fuel cell configured to provide electricity to an electrical network of the aircraft, at least a first heat exchanger belonging to the fuel circuit and configured to transmit calories from the fuel cell to the fuel flow in order to heat it, and at least one second heat exchanger mounted downstream of the first heat exchanger in the fuel circuit and configured to transmit calories from the turbomachine to the fuel flow in order to heat it.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. An MTO nvPM emissions index ratio-modified fuel flow is defined as:

[00001]$\frac{{\mathrm{EI}}_{\mathrm{maxTO},\mathrm{SAF}}}{{\mathrm{EI}}_{\mathrm{maxTO},\mathrm{FF}}}{W}_{f,\mathrm{maxTO}}$

where: EI.sub.maxTO,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); EI.sub.maxTO,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel; and W.sub.f,maxTO is the mass flow rate of fuel provided to the plurality of fuel spray nozzles in kg/s when the gas turbine engine is operating at around 100% available thrust for the given operating conditions. The MTO nvPM emissions index ratio-modified fuel flow of the gas turbine engine in kg/s is less than 2. The gas turbine engine is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

A gas turbine engine includes a combustor with a combustion chamber and fuel spray nozzles to inject fuel into the combustion chamber. The nozzles include a first and second subset. Each of the nozzles of the first subset is supplied with fuel at a greater flow rate than each of the second subset. A ratio of nozzles in the first subset to the second subset is 1:2 to 1:5. An MTO nvPM emissions index ratio-modified fuel flow is

[00001]$\frac{{\mathrm{EI}}_{\mathrm{maxTO},\mathrm{SAF}}}{{\mathrm{EI}}_{\mathrm{maxTO},\mathrm{FF}}}{W}_{f,\mathrm{maxTO}}.$

EI.sub.maxTO,SAF is nvPM emissions index in mg/kg of the engine operating at around 100% available thrust with sustainable aviation fuel. EI.sub.maxTO,FF is nvPM emissions index in mg/kg of the engine operating at around 100% available thrust with fossil-based hydrocarbon. W.sub.f,maxTO is mass flow rate of fuel to the nozzles in kg/s operating at around 100% available thrust. The MTO nvPM emissions index ratio-modified fuel flow in kg/s is less than 2.

A power plant comprises a steam system, a first electrolyzer, a heat storage system, and a heat exchanger configured to exchange thermal energy between the steam system, the first electrolyzer and the heat storage system. A method of operating an electrolyzer in a combined cycle power plant comprises operating a steam system to convert water to steam, operating an electrolyzer in a standby mode, the electrolyzer configured to convert water and electricity to hydrogen and oxygen when the electrolyzer is in an operating mode, circulating water from the steam system through a heat exchanger, circulating a first heat transfer medium between the electrolyzer and the heat exchanger, and circulating a second heat transfer medium between the heat exchanger and a thermal storage container.

A gas turbine engine includes: a rich burn, quick quench, lean burn combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An MTO nvPM emissions index ratio is defined as: $\frac{{\mathrm{EI}}_{\max \mathrm{TO},\mathrm{SAF}}}{{\mathrm{EI}}_{\max \mathrm{TO},\mathrm{FF}}}$
where: EI.sub.maxTO,SAF and EI.sub.maxTO,FF are respectively the nvPM emissions index in mg/kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the fuel spray nozzles includes a sustainable aviation fuel (SAF) or is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel including a SAF to the fuel spray nozzles. Also disclosed is a method of operating a gas turbine engine.