The present disclosure relates to systems and methods that are useful for controlling one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants and methods of carrying out a power production method utilizing different fuel chemistries. Combustion of the different fuel mixtures can be controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel chemistries.

A multi-source aircraft propulsion arrangement comprises a cryogenic propulsion source and a combustion propulsion source wherein the cryogenic propulsion source and the combustion propulsion source may be selectively and independently operated to generate propulsive force for an aircraft.

A method of operating a rotary machine below a minimum emissions compliance load in a response mode includes reducing a fuel split to zero. The fuel split apportions a total flow of fuel to the combustor between a first combustion zone and a second combustion zone. The method also includes determining a current operating temperature of the first combustion zone using a digital simulation of the rotary machine. The method further includes determining a target operating temperature of the first combustion zone. The target operating temperature enables the rotary machine to operate below a traditional Minimum Emissions Compliance Load (MECL) while still in compliance with emissions standards. The method also includes channeling a first flow of fuel to the first combustion zone. The first flow of fuel decreases the temperature of the first combustion zone to the target operating temperature.

A method of operating a rotary machine below a minimum emissions compliance load in a response mode includes reducing a fuel split to zero. The fuel split apportions a total flow of fuel to the combustor between a first combustion zone and a second combustion zone. The method also includes determining a current operating temperature of the first combustion zone using a digital simulation of the rotary machine. The method further includes determining a target operating temperature of the first combustion zone. The target operating temperature enables the rotary machine to operate below a traditional Minimum Emissions Compliance Load (MECL) while still in compliance with emissions standards. The method also includes channeling a first flow of fuel to the first combustion zone. The first flow of fuel decreases the temperature of the first combustion zone to the target operating temperature.

A process for reducing pressure of a vapor stream wherein the vapor stream rotates a turbine wheel within the turbine to transmit rotational movement to an electrical generator and generate electricity. The resulting lower pressure vapor stream reduces a partial pressure of a hydrocarbon vapor or is injected into a reactor to reduce a temperature in the reactor. A recovered electric power measuring system comprises at least one processor; at least one memory storing computer-executable instructions; and at least one receiver configured to receive data from a sensor on an electrical powerline connected to a generator of a turbine, the turbine in fluid communication with a vapor stream wherein the turbine reduces the pressure of the vapor stream and the resulting lower pressure vapor stream is injected into a reactor to reduce a temperature in the reactor or to reduce a partial pressure of hydrocarbon vapor in the reactor.

A fuel oxygen conversion unit includes a contactor defining a liquid fuel inlet, a stripping gas inlet and a fuel/gas mixture outlet; and a fuel gas separator defining a fuel/gas mixture inlet in flow communication with the fuel/gas mixture outlet of the contactor and an axis. The fuel gas separator further includes a stationary casing; and a separator assembly including a core and a plurality of paddles extending from the core, the separator assembly rotatable about the axis within the stationary casing to separate a fuel/gas mixture received through the fuel/gas mixture inlet into a liquid fuel flow and stripping gas flow.

A combustor assembly of a gas turbine engine having a trapped vortex feature to reduce emissions where the trapped vortex is formed using ammonia injected into an annular cavity located in a wall surrounding a combustion chamber of the combustor assembly. The annular cavity, and therefore the trapped vortex, is positioned such that when the combustion occurs within the combustion chamber the position of the annular cavity, and therefore of the trapped vortex, is downstream of a flame front. The emissions resulting from combustion travel through the combustion chamber and pass by the annular cavity before exiting the combustion chamber. The trapped vortex in the combustion chamber supplies NH.sub.2 radicals, resulting from the ammonia of the trapped vortex, to the passing by emissions and converts NOx and/or N.sub.2O in the emissions to non-polluting products, mainly water and nitrogen.

A combustor assembly of a gas turbine engine having a trapped vortex feature to reduce emissions where the trapped vortex is formed using ammonia injected into an annular cavity located in a wall surrounding a combustion chamber of the combustor assembly. The annular cavity, and therefore the trapped vortex, is positioned such that when the combustion occurs within the combustion chamber the position of the annular cavity, and therefore of the trapped vortex, is downstream of a flame front. The emissions resulting from combustion travel through the combustion chamber and pass by the annular cavity before exiting the combustion chamber. The trapped vortex in the combustion chamber supplies NH.sub.2 radicals, resulting from the ammonia of the trapped vortex, to the passing by emissions and converts NOx and/or N.sub.2O in the emissions to non-polluting products, mainly water and nitrogen.

An improved power generation system for aircraft and methods of its operation are provided, wherein the system combines a wave reformer providing a contiguous fuel supply to a jet engine, and use of ammonia as the fuel source from which hydrogen and/or a duel supply of ammonia and hydrogen will be supplied to aircraft jet engines leading to a higher thermal efficiency than existing engines with low to no direct emission footprint.

The present disclosure relates to systems and methods wherein a dilute hydrocarbon stream can be oxidized to impart added energy to a power production system. The oxidation can be carried out without substantial combustion of the hydrocarbons. In this manner, dilute hydrocarbon streams that would otherwise be required to undergo costly separation processes can be efficiently utilized for improving the power production system and method. Such systems and methods particularly can utilize dilute hydrocarbon stream including a significant amount of carbon dioxide, such as may be produced in hydrocarbon recovery process, such as enhanced oil recovery or conventional hydrocarbon recovery processes.