Patent classifications
B01J19/14
INSTALLATION AND METHOD FOR CONVERTING URANIUM HEXAFLUORIDE TO URANIUM DIOXIDE
An installation for the conversion of uranium hexafluoride (UF.sub.6) to uranium dioxide (UO.sub.2) comprises a hydrolysis reactor (4) for the conversion of UF.sub.6 into uranium oxyfluoride powder (UO.sub.2F.sub.2), a pyrohydrolysis furnace (6) for converting the UO.sub.2F.sub.2 powder supplied by the reactor (4) into UO.sub.2 powder, a supply device (8) comprising reagent injection ducts (10) for the injection of UF.sub.6, water vapor or H.sub.2, and a control system (16) designed to control the supply device (8) so as to supply at least one of the reagent injection ducts (10) with a neutral gas during a shut-down or start-up phase of the conversion installation.
PROCESS FOR CONVERTING A SOLID CARBON SOURCE TO GRAPHITE
The invention provides methods and apparatuses for converting a solid carbon source to graphite by precipitation from a molten metal (e.g., molten iron) as well as graphite prepared from the methods and apparatuses.
PROCESS FOR CONVERTING A SOLID CARBON SOURCE TO GRAPHITE
The invention provides methods and apparatuses for converting a solid carbon source to graphite by precipitation from a molten metal (e.g., molten iron) as well as graphite prepared from the methods and apparatuses.
Controlling aircraft inerting system
A method of controlling an inerting system of an aircraft is disclosed. The inerting system feeds inert gas into a fuel tank of the aircraft, the method includes: a) obtaining a location of the aircraft, the location comprising a current location or an expected future location; b) assessing an environmental impact of releasing of fuel vapour at the location obtained in step a); and c) controlling the inerting system based on the assessment of step b).
Controlling aircraft inerting system
A method of controlling an inerting system of an aircraft is disclosed. The inerting system feeds inert gas into a fuel tank of the aircraft, the method includes: a) obtaining a location of the aircraft, the location comprising a current location or an expected future location; b) assessing an environmental impact of releasing of fuel vapour at the location obtained in step a); and c) controlling the inerting system based on the assessment of step b).
Lattice structure for sparging evaporator in catalytic inerting system
A sparging evaporator for an inerting system including an outer vessel, an inner vessel within the outer vessel, and a plenum formed between the inner and outer vessels. The outer vessel includes a gas inlet for receiving inlet gas into the plenum, and a liquid inlet for receiving liquid fuel into the plenum. The inlet gas in the plenum generates a gas pressure that is exerted against a free surface of the liquid fuel in the plenum thereby forcing the liquid fuel and the inlet gas through an inlet of the inner vessel. The inner vessel contains a lattice structure that promotes liberation of fuel vapor from the liquid fuel and enables the inlet gas in the liquid fuel to sparge the fuel vapor in the liquid fuel, thereby forming a fuel-enriched gas mixture that can be fed to a reactor of the inerting system.
Lattice structure for sparging evaporator in catalytic inerting system
A sparging evaporator for an inerting system including an outer vessel, an inner vessel within the outer vessel, and a plenum formed between the inner and outer vessels. The outer vessel includes a gas inlet for receiving inlet gas into the plenum, and a liquid inlet for receiving liquid fuel into the plenum. The inlet gas in the plenum generates a gas pressure that is exerted against a free surface of the liquid fuel in the plenum thereby forcing the liquid fuel and the inlet gas through an inlet of the inner vessel. The inner vessel contains a lattice structure that promotes liberation of fuel vapor from the liquid fuel and enables the inlet gas in the liquid fuel to sparge the fuel vapor in the liquid fuel, thereby forming a fuel-enriched gas mixture that can be fed to a reactor of the inerting system.