Abstract: A pump arrangement for providing a saturated or subcooled liquid includes a tank for saturated liquid, a heat exchanger for cooling the saturated liquid, a pump, an expansion valve, and an output for feeding saturated or subcooled liquid to a consumer. A tank outlet is in fluid communication with a liquid inlet of the heat exchanger, such that saturated liquid stored inside the tank can flow into the heat exchanger designed to sub-cool the saturated liquid. A liquid outlet of the heat exchanger is in fluid communication with a pump inlet. The expansion valve outlet is in fluid communication with a coolant inlet of the heat exchanger. An expansion valve inlet is arranged for receiving and expanding a fraction of liquid flowing through the pump arrangement and routing it into the coolant input to at least partially evaporate and receive evaporation enthalpy of the liquid to be subcooled.

Abstract: A fuel system for a liquefied gas drive system. The fuel system has a liquefied gas tank and a cooling system for the vaporized content of liquefied gas, which comprises a liquid nitrogen tank, a nitrogen pump, a heat exchanger, and a nitrogen cooler, which are connected to each other in a pipework circuit. The heat exchanger is arranged in the interior of the liquefied gas tank. Also disclosed are a vehicle, a plant and a machine, in each case with a fuel system, and a method for cooling the vaporized content of liquefied gas of a liquefied gas drive system.

Abstract: A gas injection device for injecting an expulsion gas into a tank for a liquid. The gas injection device comprises an inlet pipe for receiving the gas and a distributor portion for releasing the gas through a plurality of capillary passages. The inlet pipe has a first end configured to be connected to a gas supply line and a second end located within a chamber in the distributor portion. The capillary passages respectively extend in a direction adapted to a periphery of the chamber. A tank for a liquid is provided, the tank comprising a gas injection device. A spacecraft is provided comprising such a tank.

Abstract: A fuel system for a liquefied gas drive system. The fuel system has a liquefied gas tank and a cooling system for the vaporized content of liquefied gas, which comprises a liquid nitrogen tank, a nitrogen pump, a heat exchanger, and a nitrogen cooler, which are connected to each other in a pipework circuit. The heat exchanger is arranged in the interior of the liquefied gas tank. Also disclosed are a vehicle, a plant and a machine, in each case with a fuel system, and a method for cooling the vaporized content of liquefied gas of a liquefied gas drive system.

Abstract: A tank or tank system for storing a cryogenic liquid exhibiting at least one collecting container with an upper region and a lower region, so as to hold the cryogenic liquid, at least one arrangement for feeding and discharging liquids and at least one arrangement for feeding and discharging gases, wherein the tank further exhibits at least one frame structure comprising a thermal insulation material.

Abstract: A gas injection device for injecting an expulsion gas into a tank for a liquid. The gas injection device comprises an inlet pipe for receiving the gas and a distributor portion for releasing the gas through a plurality of capillary passages. The inlet pipe has a first end configured to be connected to a gas supply line and a second end located within a chamber in the distributor portion. The capillary passages respectively extend in a direction adapted to a periphery of the chamber. A tank for a liquid is provided, the tank comprising a gas injection device. A spacecraft is provided comprising such a tank.

Abstract: A tank or tank system for storing a cryogenic liquid exhibiting at least one collecting container with an upper region and a lower region, so as to hold the cryogenic liquid, at least one arrangement for feeding and discharging liquids and at least one arrangement for feeding and discharging gases, wherein the tank further exhibits at least one frame structure comprising a thermal insulation material.

Abstract: A separator tank for separating and retaining a liquid phase from a liquid-gas fluid mixture is suitable for use with cryogenic as well as non-cryogenic liquids, in space experiments or other applications under weightless conditions. The separator tank has liquid storage members of porous, sponge-like metal foam arranged in a tank vessel. The total pore volume and porosity characteristics of the metal foam are selected to provide capillary uptake greater than the total volume of the liquid to be retained. In a preferred example, the liquid storage members are coaxially arranged, radially spaced, annular cylindrical members, with flow passage notches at alternating opposite ends thereof, to form a meandering fluid flow path therebetween. A gas extraction device is provided at the center of the tank. The separator tank and an upstream connected fluid supply tank can be arranged within a cryostat.

Abstract: A separator tank for separating and retaining a liquid phase from a liquid-gas fluid mixture is suitable for use with cryogenic as well as non-cryogenic liquids, in space experiments or other applications under weightless conditions. The separator tank has liquid storage members of porous, sponge-like metal foam arranged in a tank vessel. The total pore volume and porosity characteristics of the metal foam are selected to provide capillary uptake greater than the total volume of the liquid to be retained. In a preferred example, the liquid storage members are coaxially arranged, radially spaced, annular cylindrical members, with flow passage notches at alternating opposite ends thereof, to form a meandering fluid flow path therebetween. A gas extraction device is provided at the center of the tank. The separator tank and an upstream connected fluid supply tank can be arranged within a cryostat.

Abstract: In a propellant tank, which especially stores cryogenic propellants, for example a fuel or an oxidizer for a spacecraft, and which operates with a driving gas to drive or convey the propellant, the propellant is separated from the driving gas in a propellant extraction apparatus using sieves with hydrostatic forces and capillary forces. The extraction apparatus includes a refillable reservoir, which is mounted near the tank floor outside of the tank shell, and which is connected via plural holes with the interior of the propellant tank. The extraction apparatus includes a double-walled housing that is thermally insulated. Capillary plates and struts are inserted in an L-shape into the reservoir. To substantially prevent the penetration of gas out of the propellant line, a cylinder-shaped pleated sieve is mounted at the end of the propellant line.

Abstract: A bubble trap is especially suitable for separating gas bubbles from liquid fuel supplied from a fuel tank in a spacecraft. The bubble trap includes a rotationally symmetrical collecting container forming a container wall, plural liquid guide vanes extending radially and longitudinally along the inside of the container wall, a perforated conical gas separator that tapers conically toward an outlet of the collecting container, and screens arranged between the gas separator and the outlet.

Abstract: A tank arrangement includes a tank for storing a liquid such as fuel or oxidizer for operation of a spacecraft and a pressurized driving gas for conveying the liquid out of the tank, and a gas supply and extraction device. The device includes a housing shell and plural outwardly expanding passage bodies providing openings that communicate the interior space of the tank to the inner reservoir space of the device. A baffle plate shields the outer opening of each passage body. Deflector plates are arranged in each passage body. Capillary plates extend longitudinally along the inner wall of the housing shell. By a capillary effect, the plates separate liquid from gas entering the device, so that the gas can be extracted while the liquid is stored in a reservoir of the device until it is drained back into the tank during an accelerated operation phase of the spacecraft.

Abstract: A gas supply and extraction device is arranged preferably on a tank lid or a tank wall in a tank for storing a pressurized driving gas and a liquid such as fuel or oxidizer for operation of a spacecraft. A device housing defines an interior reservoir space. Upper trumpet-shaped passage bodies and a lower trumpet-shaped passage body communicate from the interior reservoir space into the interior space of the tank. By capillary effects, baffle plates, deflector plates, capillary plates, a separation chamber and other components separate liquid from gas entering the device, so that the gas can be extracted while the liquid is stored in the reservoir space of the device until it is drained back into the tank during an accelerated operation phase of the spacecraft.

Abstract: A bubble trap is especially suitable for separating gas bubbles from liquid fuel supplied from a fuel tank in a spacecraft. The bubble trap includes a rotationally symmetrical collecting container forming a container wall, plural liquid guide vanes extending radially and longitudinally along the inside of the container wall, a perforated conical gas separator that tapers conically toward an outlet of the collecting container, and screens arranged between the gas separator and the outlet.

Abstract: A gas supply and extraction device is arranged preferably on a tank lid or a tank wall in a tank for storing a pressurized driving gas and a liquid such as fuel or oxidizer for operation of a spacecraft. A device housing defines an interior reservoir space. Upper trumpet-shaped passage bodies and a lower trumpet-shaped passage body communicate from the interior reservoir space into the interior space of the tank. By capillary effects, baffle plates, deflector plates, capillary plates, a separation chamber and other components separate liquid from gas entering the device, so that the gas can be extracted while the liquid is stored in the reservoir space of the device until it is drained back into the tank during an accelerated operation phase of the spacecraft.

Abstract: A fuel tank of a spacecraft stores a liquid fuel and a pressurized propellant gas that drives the fuel out of the tank though a fuel extraction arrangement including a reservoir or fuel collection container and a tank outlet. A spiraling or J-shaped or hook-shaped fuel collection channel and plural obliquely sloping fuel flow channels connect the fuel collection container to an outlet pipe of the tank outlet. The channels are configured, dimensioned, oriented and arranged to ensure that fuel will be retained in the outlet pipe without leaking back into the fuel tank, even when the tank is oriented horizontally and has a low tank filling level. These structures produce a capillary pumping effect and use the surface tension to separate the fuel from the propellant gas, and allow the inner space of the collection container to be completely filled with liquid fuel.

Abstract: In a propellant tank, which especially serves for storing cryogenic propellants, for example of spacecraft, and which is operated with a driving gas serving as a conveying medium, the separation of the propellant from the driving gas occurs in a propellant extraction apparatus by means of sieves and with the use of hydrostatic forces and capillary forces. The extraction apparatus has the form of a refillable reservoir, which is mounted in the vicinity of the tank floor outside of the tank shell on the floor region of the propellant tank, and which is connected via a number of holes with the interior of the propellant tank. The extraction apparatus itself consists of a double-walled housing and is additionally thermally insulated. Capillary plates and additional struts are inserted in an L-shape into the reservoir. Furthermore, to substantially prevent the penetration of gas out of the propellant line, a cylinder-shaped pleated sieve is mounted at the end of the propellant line.

Abstract: A tank arrangement includes a tank for storing a liquid such as fuel or oxidizer for operation of a spacecraft and a pressurized driving gas for conveying the liquid out of the tank, and a gas supply and extraction device. The device includes a housing shell and plural outwardly expanding passage bodies providing openings that communicate the interior space of the tank to the inner reservoir space of the device. A baffle plate shields the outer opening of each passage body. Deflector plates are arranged in each passage body. Capillary plates extend longitudinally along the inner wall of the housing shell. By a capillary effect, the plates separate liquid from gas entering the device, so that the gas can be extracted while the liquid is stored in a reservoir of the device until it is drained back into the tank during an accelerated operation phase of the spacecraft.