Described herein are at least systems and methods for cryogenic fluid delivery which utilize pumpless delivery of cryogenic fluid. The systems and methods utilize hydraulic pressure, saturation pressure, or a combination of both hydraulic pressure and saturation pressure to deliver cryogen to a use device, such as an engine.

A method and apparatus are provided for operating a refueling station including source tube-trailers and at least one compressor to reduce refueling cost. The refueling station includes a gaseous fuel supply source including a plurality of tanks on a tube trailer coupled to a first control unit, and high pressure buffer storage having predefined capacity coupled to a second control unit and the first tanks by a pressure control valve and the first control unit, and at least one compressor. The refueling station is operated at different modes depending on a state of the refueling station at the beginning of each operational mode. The refueling system is assessed at the end of each operational mode to identify the state of the system and select a next mode of operation. The operational modes include consolidating hydrogen, or any gaseous fuel, within the tubes mounted on the trailer.

Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) connected to the primary volume (V1) via a valve (20) configured to selectively allow a passage of fluid from the primary volume (V1) to the secondary volume (V2), or to isolate the secondary volume (V2) from the primary volume (V1), the primary volume (V1) having a primary orifice (11) adapted to be connected to a first pressurization source (41), the secondary volume (V2) having a supply orifice (4) adapted to be connected to a supply line of a spacecraft engine (30), and a secondary orifice (12) adapted to be connected to a second pressurization source (42).

A system and method for maintaining overpressure in a logging unit or other pressurized space through interruptions is disclosed. A backup air supply comprising tanks mounted to a frame is operatively connected to the ambient environment of the logging unit through a valve assembly which also connects a conventional pressure setup (e.g., pumps and filters from the external environment). The valve assembly comprises two auto valves, a shuttle valve, and a pressure sensor that allow the logging unit to switch from the conventional external air supply to the tanks when the pressure detected from the conventional air supply falls below a predetermined level. The valve assembly is independently housed and may be mounted or detached from the frame housing the backup tanks.

An environmentally friendly fuel distribution station includes an upper canopy, said upper canopy including a fuel tank and an outer shell enclosing said fuel tank, and a fuel distribution interface suspended from said upper canopy, said fuel distribution interface selectively distributing fuel from said fuel tank during a fueling operation.

The present invention is directed to a new concept for a large-scale high-pressure Honeycomb Set Tank in an ISO container and for its manufacturing facilities. A process for manufacturing a plurality of honeycomb cells with a high degree of accuracy is also provided.

The invention relates to a pneumatic emergency shutdown system for a liquefied gas supply arrangement in which liquefied gas is supplied between a first tank and a second tank. The pneumatic emergency shutdown system comprises a pneumatic emergency shutdown circuit comprising pressure medium and provided in connection with the first tank and a pneumatic emergency shutdown link provided to the pneumatic emergency shutdown circuit, said a pneumatic emergency shutdown link connecting the pneumatic emergency shutdown circuit to a pneumatic controlling system of the second tank.

Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) connected to the primary volume (V1) via a valve (20) configured to selectively allow a passage of fluid from the primary volume (V1) to the secondary volume (V2), or to isolate the secondary volume (V2) from the primary volume (V1), the primary volume (V1) having a primary orifice (11) adapted to be connected to a first pressurization source (41), the secondary volume (V2) having a supply orifice (4) adapted to be connected to a supply line of a spacecraft engine (30), and a secondary orifice (12) adapted to be connected to a second pressurization source (42).

A system and a method for filling a tank are provided. The tank filling system includes tanks that are filled with predetermined fluid and a manifold that is coupled to each of the plurality of tanks in a communication manner. A first flow passage is connected to a first inlet of the manifold to supply the fluid to be filled into the plurality of tanks to the manifold and a second flow passage is connected to a second inlet of the manifold spaced apart from the first inlet of the manifold by a predetermined distance to supply the fluid to be filled into the plurality of tanks to the manifold. A controller opens and closes the first flow passage and the second flow passage.

A gas supply marine vessel and a refueling facility are described. The gas supply marine vessel includes a hull with an upper deck having an elongated cargo cavity formed therein. Gas interface modules are disposed in the cavity and extend between hull sides, each module having a plurality of fuel vessel docking stations. A plurality of stacked fuel container assemblies are fluidically coupled to the docking stations. A gantry, is movable along the length of the cavity, straddles the cargo cavity between hull sides. An articulating crane is mounted on the gantry and it utilized to move fuel container assemblies to a fuel container depression formed in the deck of a floating refueling facility. The floating refueling facility includes a concave side to facilitate mooring adjacent a shoreline, the concave side forming angled extensions at corners of the deck with a linkspan extending from each of the angled extensions.