A method of manufacturing a high-pressure composite pressure vessel for high-pressure being at or above 70 bar (1000 PSI or 7 MPa) includes providing an expandable core vessel defining a hoop section between end domes. An aligned discontinuous fiber composite material is wrapped over the expandable core vessel aligning with a plurality of load paths present in the expandable core vessel being over the hoop section and end domes. The aligned discontinuous fiber composite material has fibers in a prepreg tape that are at least 5 mm in length to 100 mm in length or less. Next, a continuous fiber-reinforced composite is wrapped over the aligned discontinuous fiber-reinforced composite along the hoop section and not wrapped along the end domes. The expandable core vessel may be pressurized and heated to consolidate the composite overwrap. Finally, the vessel is cooled under pressure resulting in the high-pressure composite pressure vessel.

A sealed and thermally insulating tank including a thermally insulating barrier suitable for being anchored to a load-bearing structure is disclosed. The thermally insulating barrier including a plurality of insulating panels juxtaposed in a regular pattern, two adjacent insulating panels defining an inter-panel space, the inter-panel space including an outer portion and an inner portion superposed in the direction of the thickness of the thermally insulating barrier, the outer portion being suitable for being situated close to the load-bearing structure and the inner portion being close to the inside of the tank, the tank further including insulating seals, the insulating seals including two outer insulating seals, the said outer insulating seals being arranged juxtaposed in the outer portion of the inter-panel space so that they have two adjacent edges, and an inner insulating seal, the inner insulating seal being arranged in the inner portion of the inter-panel space.

A tank is used in the containment, transport, and/or storage of fluids, e.g., one or more liquids and/or gases. In one embodiment, the tank includes a plurality of segments collectively defining an interior chamber that retains the fluid(s), each of which includes opposing ends defining beveled mating surfaces. The tank also includes a plurality of endcaps positioned between, and in engagement with, adjacent segments, as well as a plurality of webs that include a series of first webs having a first configuration and a series of second webs having a second, different configuration. The first webs are positioned within the plurality of segments between the ends thereof, and the second webs are positioned within the endcaps. In an alternate embodiment, the tank is devoid of the endcaps, and instead, includes segments defining beveled mating surfaces that intersect at junctures to define four corner sections of the tank.

The present invention relates to a computer-implemented method and system for computing a transition parameter of a liquefied gas storage medium, the storage medium having at least one sealed and unrefrigerated tank, the transition parameter characterizing an evolution of a two-phase mixture contained in the sealed and unrefrigerated tank between an initial state and a final state, the two-phase mixture including a liquid phase and a vapour phase, the transition parameter may be a duration of the transition, a liquid bleeding rate or a vapour bleeding rate.

The invention is a reservoir for the storage of a pressurized fluid such as compressed air notably to the storage and recovery of energy using compressed air. In particular, the reservoir comprises at least one tube formed of an arrangement of concentric layers (C1, C2, C3, C4). This arrangement comprises, working from the inside toward the outside of the tube, an internal layer (C1) formed of concrete, a layer (C2) formed of steel of thickness E, at least one layer (C3) formed by a winding of steel wires (C3″) on a sublayer (C3′) of concrete, and an external layer (C4) which protects the wires against at least one of physical and chemical damage, and in which the wires are subjected to circumferential (hoop) tensile prestress with at least one of the thickness E and the prestress being rated to withstand the pressure of pressurized fluid.

The invention relates to a sealed and thermally insulating tank wall comprising a thermally insulating barrier defining a support surface for a sealing membrane, the thermally insulating barrier comprising two adjacent insulating panels jointly delimiting an inter-panel space, the tank wall further comprising an insulating insert arranged in the inter-panel space so as to fill the inter-panel space, the insulating insert comprising an insulating core at least partially covered by a wrapper, the insulating core comprising layered glass wool, the layered glass wool comprising laps of fibers superposed in a direction of layering, the insulating insert being arranged in the inter-panel space in such a way that the direction of layering of the layered glass wool is parallel to a widthwise direction of the inter-panel space.

The invention relates to a method for manufacturing a sealed and thermally insulating tank wall comprising: providing a thermally insulating barrier comprising two insulating panels delimiting an inter-panel space, providing an insulating insert comprising a wrapper completely covering an insulating core, inserting a suction nozzle of a suction system into the insulating insert through an orifice in the wrapper, applying a vacuum pressure in the insulating insert so as to reduce the thickness of the insulating insert through vacuum pressure, inserting the insulating insert into the inter-panel space while maintaining the suction of the suction system, when the insulating insert has been inserted into the inter-panel space, removing the suction nozzle from the insulating insert.

A cryogenic fluid pressure vessel for an aircraft, having: a first wall layer, which contains carbon fiber-reinforced plastic, having an inner contact surface for the contact with a pressurized cryogenic fluid to be accommodated inside the cryogenic fluid pressure vessel; a second wall layer, which is arranged on an outer surface of the first wall layer and has a thermal barrier; a closable inlet/outlet opening for cryogenic fluid, which extends through the first and the second wall layer; and a structural insert integrated in the first and the second wall layer, which has a fastening connecting piece located on the outside of the cryogenic fluid pressure vessel for mechanically coupling the cryogenic fluid pressure vessel with external structures; wherein the cryogenic fluid pressure vessel forms an essentially cylindrical main body. Furthermore, the present invention provides an aircraft having such a cryogenic fluid pressure vessel.

A tank that has a tank wall having a secondary insulating barrier, a primary insulating barrier, a primary sealed membrane and a secondary sealed membrane, the tank wall having a first area in which the insulating modules include spacers extending in a thickness direction of the tank wall between a cover panel and a bottom panel of said insulating modules, a second area in which a cover panel of the insulating modules is kept at a distance from a bottom panel by a structural insulating foam, a transition area interposed between the first area and the second area, the transition area having a coefficient of thermal contraction and/or a modulus of elasticity in the thickness direction of the tank wall which is between that of the first area and that of the second area.

The present invention relates to a gas treatment system and a ship including the same. The gas treatment system treats liquefied gas as heavier hydrocarbons or ammonia. The gas treatment system includes: a fuel tank storing liquefied gas as a fuel to be supplied to a propulsion engine of a ship; a liquefied gas supply line supplying the liquefied gas of the fuel tank in a liquid phase to the propulsion engine, the liquefied gas supply line having a high pressure pump provided thereon; a reliquefaction apparatus liquefying boil-off gas generated in a cargo tank storing liquefied gas; and a liquefied gas collection line collecting the liquid liquefied gas discharged from the propulsion engine upstream of the high pressure pump. The reliquefaction apparatus transfers the liquefied boil-off gas to the fuel tank, thereby allowing the liquefied boil-off gas to be supplied to the propulsion engine by the high pressure pump.