The jacking system and method for using it to lower an upper column section without the use of a crane is provided. The jacking system is configured to be disposed on a roof of a cold box module and may include: a structural assembly; and a plurality of suspension rods supported at an upper end by the structural assembly, wherein the plurality of suspension rods is configured to provide support to the upper column section

The invention relates to a method for separating a liquefiable gas mixture consisting of a plurality of components, comprising at least one first component (K1) and one second component (K2), wherein, under an increased pressure p.sub.1, the first component (K1) has a melting point T*.sub.K1 that is higher than the melting point T*.sub.K2 of the second component (K2). In order to realise a configuration that is as compact as possible, it is provided in accordance with the invention that the method comprises the following steps: converting the gas mixture to a liquid state at a temperature T.sub.0 and a pressure p.sub.0, wherein T*.sub.K2<T.sub.0T*.sub.K1 and p.sub.0<p.sub.1 applies, and wherein the first component (K1) is present in an initial concentration (C0); producing a pressure gradient in the liquefied gas mixture, wherein the increased pressure p.sub.1 prevails at least in a limited spatial region (3) of the liquefied gas mixture, and freeze separation of the first component (K1) occurs.

A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

A ground-based cryogenic cooling system includes a means for cooling an airflow and producing chilled air responsive to a power supply. A liquid air condensate pump system is operable to condense the chilled air into liquid air and urge the liquid air through a feeder line. A cryogenic cartridge includes a coupling interface configured to detachably establish fluid communication with the feeder line and a cryogenic liquid reservoir configured to store the liquid air under pressure. The cryogenic cartridge can be coupled to a cryogenic liquid distribution system on an aircraft. The liquid air can be selectively released from the cryogenic cartridge through the cryogenic liquid distribution system for an aircraft use.

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 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.