In a system and a method for pressure management while extracting a liquid from a liquid storage vessel, a liquid and its vapor are provided in liquid storage vessel. The liquid is extracted by a pump from the storage vessel and fed as a liquid flow to a consumer unit. A defined partial flow is separated from the liquid flow downstream of the pump. The pressure of the partial flow is reduced by a pressure regulation means and the partial flow is evaporated by an evaporator. The evaporated partial flow is fed back into the storage vessel.

A hydrogen fuel supply system 1 comprises a tank 2 which stores liquid hydrogen therein; a supply line 4 which takes the liquid hydrogen out of the tank 2, vaporizes the liquid hydrogen into a hydrogen gas, and supplies the hydrogen gas to a use point 3; and a pressurization line 5 which compresses the hydrogen gas generated by vaporization of the liquid hydrogen inside the tank 2 by use of a compressor 59 so that a pressure of the hydrogen gas is increased, and sends the hydrogen gas with the increased pressure to a gaseous phase part inside the tank 2.

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 catalytic tank heater includes a catalytic heating element supported on an LPG tank by a support structure that holds the element in a position facing the tank. Vapor from the tank is provided as fuel to the heating element, and is regulated to increase heat output as tank pressure drops. The heating element is internally separated into a pilot heater and a main heater, with respective separate fuel inlets. The pilot heater remains in continual operation, but the main heater is operated only while tank pressure is below a threshold. Operation of the pilot heater keeps a portion of the catalyst hot, so that, when tank pressure drops below the threshold, and fuel is supplied to the main heater, catalytic combustion quickly expands from the area surrounding the pilot heater to the remainder of the catalyst.

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 cryogenic fluid delivery system includes a main tank system with a main tank adapted to contain a first supply of cryogenic liquid, and reserve tank system with reserve tank adapted to contain a second supply of cryogenic liquid. A pressure building circuit is adapted to delivery vapor to the head space of the main tank to build pressure in the main tank and a fuel delivery line supplies cryogenic fuel from either the main tank or the reserve tank to a use device. The reserve tank stores saturated cryogenic fuel that is delivered to the use device via the fuel delivery line while the cryogenic liquid in the main tank is being saturated. The fluid delivery system automatically switches to delivering cryogenic fuel from the main tank to the use device via the fuel delivery line upon saturation of the cryogenic liquid in the main tank.

A method for filling a tank (1) with liquefied gas, in particular a tank with cryogenic liquid, from a liquefied gas container (2), in particular a cryogenic liquid container (2), wherein, following a predetermined time after filling has started, the method comprises the step of comparing the first instantaneous pressure (PT3) in the filling pipe (3) or an average of said first instantaneous pressure (PT3) with a predetermined maximum threshold (Pmax), and, when said first instantaneous pressure (PT3) in the filling pipe (3) or the average of said first instantaneous pressure (PT3), respectively, exceeds the maximum threshold (Pmax), the step of interrupting (AR) the filling (R).

A method for filling a tank (1) with liquefied gas, in particular a tank with cryogenic liquid, from a liquefied gas container (2), in particular a cryogenic liquid container (2), which container (2) is in fluid communication with the tank (1) via a filling pipe (3), wherein the method uses a pressure differential generation member (4) for transferring liquid from the container (2) to the tank (1) at a predetermined pressure, characterized in that, at or following the switching on time (M) of the pressure differential generation member (4), the method comprises a step of determining the pressure (PT4) in the tank (1) via a measurement of a first pressure in the filling pipe (3), and, following the determination of the pressure (PT4) in the tank, a step of limiting the first instantaneous pressure (PT3) to a level below a maximum pressure threshold (PT3sup), said maximum pressure threshold being defined on the basis of the determined value of the pressure (PT4) in the tank (1) and exceeding said determined value of the pressure (PT4) in the tank by two to twenty bars and preferably by two to nine bars.

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).

The present disclosure provides a system for managing a pressure in an underground cryogenic liquid storage tank and a method for the same. The system includes: a storage tank, which is used for containing cryogenic liquid and is buried underground; an internal pump, which is located below a liquid level of the cryogenic liquid; an evaporator, provided with an upstream end which is in communication with a discharge end of the internal pump and a downstream end which is in communication with a head space via a vapor delivery line; a control valve, which is disposed on the vapor delivery line downstream of the evaporator; and a flow limiter, which is disposed on the vapor delivery line upstream of or downstream of the control valve. The present disclosure can realize efficient pressurization to the storage tank so as to prevent collapsing of the storage tank.