A duct is provided and includes a tubular member having an inlet portion, an outlet portion and a central portion interposed between the inlet and outlet portions and a tributary tubular member fluidly coupled to the tubular member at the central portion. The tributary tubular member includes first and second torus sectors defining first and second apertures, respectively, through which an upstream end of the central portion extends. The second torus sector is disposed within the first torus sector to define a sectioned toroidal annulus about the first and second apertures and between an exterior surface of the second torus sector and an interior surface of the first torus sector.

A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.

An air cycle machine includes an air inlet connected to an air cycle compressor. Air downstream of the air cycle compressor is connected to be delivered across a first turbine. The air cycle compressor is driven by the first turbine through a shaft. Air downstream of the first turbine is connected to a second turbine. The second turbine is connected to deliver air downstream. The second turbine is connected with a second shaft to drive a fan rotor. The fan rotor delivers a source of air across a primary heat exchanger positioned between the inlet and the air cycle compressor. The air cycle compressor and the first turbine are formed of a metal. The second turbine and the fan rotor are formed of non-metallic materials.

Various systems and methods for suppling cryogenic refrigeration to supercomputing applications such as quantum computing operations are provided. The disclosed systems and methods are flexible, efficient and scaleable to meet the cryogenic refrigeration requirements of many supercomputing applications. The disclosed systems and methods include: (i) a liquid nitrogen based integrated refrigeration system that integrates a nitrogen refrigerator with a refrigeration load circuit; (ii) a closed loop liquid nitrogen based refrigerator that provides cooling to the refrigeration load circuit via indirect heat exchange between liquid nitrogen in a nitrogen refrigerator and a separate refrigerant in a closed-loop refrigeration load circuit; and (iii) a liquid air based integrated refrigeration system that integrates an air intake system with a refrigerator and a refrigeration load circuit.

An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

The storage device is adapted to store a plurality of objects, such as sample tube holders, at several low temperatures, e.g., at −80° C. and at −110° C. The storage device includes a storage chamber with a plurality of storage cassettes arranged in its bottom section. A cassette lift in its top section can be used to lift individual storage cassettes up and to move them to an access opening, where the contents of the storage cassette can be accessed. The bottom section is divided into several, concentric storage zones, with the innermost, first storage zone being colder than the outer, second storage zone. A first insulating wall separates the two storage zones. This design reduces the thermal losses of the storage device. A refrigerant circuit with a non-inflammable cryo-liquid is provided for carrying off heat from the first storage zone.

A cooling system and method including a cooling chamber with an air inlet, a water inlet, and a cooling fill disposed between the air inlet and the water inlet. The cooling fill configured to put more water surface area in contact with air. The cooling system also including a basin disposed on a side of the cooling fill that is opposite the water inlet, the basin configured to collect the water from the cooling fill. A precooler is included in combination with the basin, the precooler including a heat-mass exchanger in combination with the basin, a blower configured to provide pressurized air through the heat-mass exchanger, and an expansion device configured to depressurize the air after the heat-mass exchanger.

A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.

An air turbo-refrigeration unit includes a compressor on die same shaft as a turbo-expander, an electric motor, a two-cavity heat exchanger, a recuperator, a water trap, and a refrigeration chamber with a cooler and a fan. The unit has a two-cavity heat exchanger/cooler and second and third water traps. The compressor is connected by its outlet to the first cavity of the heat exchanger, which connects to the first cavity of the heat exchanger/cooler. The first cavity of the heat exchanger/cooler is connected via the second water trap to the first cavity of the recuperator, which communicates with the inlet of the turbo-expander via the first water trap. The turbo-expander is connected by its outlet via the third water trap to the second cavity of the heat exchanger/cooler, which communicates with the cooler and, via the cooler, with the second cavity of the recuperator, which communicates with the compressor inlet.

An air cycle machine includes a compressor in fluid communication with a load cooling heat exchanger, a first valve and a first turbine connecting the compressor to the load cooling heat exchanger, and a second valve and a second turbine. The second valve and the second turbine connect the compressor to the load cooling heat exchanger and connected in parallel with the first valve and the first turbine between the compressor and the load cooling heat exchanger. Air cycle machine systems and methods of controlling air flow through air cycle machines are also described.