The present disclosure relates to a power production system that is adapted to achieve high efficiency power production with complete carbon capture when using a solid or liquid hydrocarbon or carbonaceous fuel. More particularly, the solid or liquid fuel first is partially oxidized in a partial oxidation reactor. The resulting partially oxidized stream that comprises a fuel gas is quenched, filtered, cooled, and then directed to a combustor of a power production system as the combustion fuel. The partially oxidized stream is combined with a compressed recycle CO.sub.2 stream and oxygen. The combustion stream is expanded across a turbine to produce power and passed through a recuperator heat exchanger. The expanded and cooled exhaust stream is scrubbed to provide the recycle CO.sub.2 stream, which is compressed and passed through the recuperator heat exchanger and the POX heat exchanger in a manner useful to provide increased efficiency to the combined systems.

A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine engine further includes a means for selectively releasing a cooling fluid flow produced at a cryogenic temperature and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section and the turbine section.

An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.

A process for cryogenic air separation and liquefaction, including purifying and compressing an inlet air stream, thereby producing a compressed inlet air stream, dividing the compressed inlet air stream into an ASU portion and a liquefaction portion, introducing the ASU portion into an air separation unit, thereby producing a gaseous oxygen steam and a gaseous nitrogen stream, and introducing the liquefaction portion, the gaseous oxygen steam and the gaseous nitrogen stream into a liquefaction unit, thereby producing a liquid nitrogen stream and a liquid oxygen stream. Wherein, the air separation unit is located more than 200 meters from the liquefaction unit, and there is no compression driven by external energy within 200 meters of the liquefaction unit.

A system for generating an inert fluid, the system being carried on board an aircraft, the generation system including a plurality of devices configured each, in succession, to execute a separation of components of a primary fluid initially collected in the form of compressed hot air, the system including at least one heat exchanger configured to execute a separation of components, by change of phase of a component of the primary fluid, executing a cooling of the primary fluid using liquid hydrogen, supplied with liquid hydrogen collected from a tank of the aircraft. It is thus possible to generate an inert gas without requiring membrane separation of the nitrogen and the oxygen, and while at the same time making it easier to warm the liquid hydrogen stored and used in the aircraft as a source of energy.