A hydrogen/oxygen stoichiometric combustion turbine system includes: a high-pressure steam turbine (2); a low-pressure steam turbine (3); and a heater (5) disposed between the high-pressure and low-pressure steam turbines. The heater (5) has a combustion portion (53) in which stoichiometric combustion of hydrogen and oxygen is caused, and a mixing portion (55) configured to mix discharged steam (S4) from the high-pressure steam turbine (2) with combustion gas (R) from the combustion portion (53) and to supply the obtained product to the low-pressure steam turbine (3).

A fuel oxygen reduction unit is provided for reducing an oxygen content of a flow of liquid fuel to an engine. The fuel oxygen reduction unit includes: a stripping gas supply line for providing a flow of stripping gas; a contactor defining a liquid fuel inlet, a stripping gas inlet and a fuel/gas mixture outlet, the stripping gas supply line in airflow communication with the stripping gas inlet; a means for modulating the flow of stripping gas through the stripping gas supply line; and a controller operable with the means for modulating the flow of stripping gas through the stripping gas supply line to modulate the flow of stripping gas through the stripping gas supply line in response to an engine operability parameter.

Aircraft systems including a fuel tank containing a cryogenic fuel, an engine configured to consume the fuel, and an ECS having a precooler arranged to receive the fuel and air from the engine. The precooler includes a first heat exchanger configured to receive a first state of the fuel and output a second state of the fuel and a second heat exchanger configured to receive the second state fuel and output a third state fuel. The first state has a first density, the second state has a second density, and the third state has a third density, wherein the first density is greater than the second density, and the second density is greater than the third density. The engine air is directed through the second heat exchanger first and then through the first heat exchanger.

Turbine engine systems are described. The turbine engine systems include a combustor arranged along a core flow path of the turbine engine, a cryogenic fuel tank configured to supply a fuel to the combustor, a fuel supply line having a first flow supply line and a second flow supply line, the first flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a first core flow path heat exchanger, and the second flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a second core flow path heat exchanger, and a flow controller arranged along the fuel supply line and configured to respectively control a flow of fuel into the first flow supply line and the second flow supply line.

Turbine engine systems are described. The turbine engine systems include a combustor arranged along a core flow path of the turbine engine, a cryogenic fuel tank configured to supply a fuel to the combustor, a fuel supply line having a first flow supply line and a second flow supply line, the first flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a first core flow path heat exchanger, and the second flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a second core flow path heat exchanger, and a flow controller arranged along the fuel supply line and configured to respectively control a flow of fuel into the first flow supply line and the second flow supply line.

An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.

An aircraft system includes a turbine engine having a compressor, a combustor having an inlet and an outlet, and a turbine having an inlet portion and an outlet portion. An auxiliary power unit (APU) is operatively connected to the turbine engine. The APU includes a compressor portion, a generator, and a turbine portion. The compressor portion is operatively connected to the turbine portion through the generator. A source of cryogenic fluid is operatively connected to the turbine engine and the APU. A heat exchange member includes an inlet section operatively connected to the source of cryogenic fluid, a first outlet section operatively connected to the turbine engine and a second outlet section operatively connected to the compressor portion.

A gas turbine engine includes a cracking device that is configured to decompose a portion of an ammonia flow into a flow of component parts of the ammonia flow, a thermal transfer device that is configured to heat the ammonia flow to a temperature above 500° C. (932° F.), a combustor that is configured to receive and combust the flow of component parts of the ammonia flow to generate a high energy gas flow, a compressor section that is configured to supply compressed air to the combustor, and a turbine section in flow communication with the high energy gas flow produced by the combustor and mechanically coupled to drive the compressor section.

A gas turbine engine includes a cracking device that is configured to decompose a portion of an ammonia flow into a flow of component parts of the ammonia flow, a thermal transfer device that is configured to heat the ammonia flow to a temperature above 500° C. (932° F.), a combustor that is configured to receive and combust the flow of component parts of the ammonia flow to generate a high energy gas flow, a compressor section that is configured to supply compressed air to the combustor, and a turbine section in flow communication with the high energy gas flow produced by the combustor and mechanically coupled to drive the compressor section.

A system for producing high purity carbon monoxide and hydrogen as well as activated carbon includes a pyrolysis reactor, a gasifier, a combustion turbine, a boiler, a steam turbine, a combined cycle unit and an electrolysis unit. Liquid fuel from the pyrolysis reactor is provided to the combustion turbine. Liquid and gaseous fuels are provided to the boiler. Compressed oxygen from the electrolysis unit is provided to the combustion turbine. Electric power from the combustion turbine and steam turbine are provided to the electrolysis unit. The gasifier includes a preheat region, a gasification region, and a cooling region. CO.sub.2 and O.sub.2 are injected into the gasifier at multiple injection levels to create an isothermal gasification region to produce CO. The CO.sub.2 and O.sub.2 are preheated in a heat exchanger using the CO exiting from the gasifier prior to injection.