A device heating a fluid and usable in a rocket launcher to pressurize a liquefied propellant. The device includes a first burner performing first combustion between a limiting propellant and an excess propellant; a first heat exchanger in which first burnt gas from the first combustion transfers heat to the fluid; at least one second burner into which both the first burnt gas and some limiting propellant are injected to perform second combustion between the limiting propellant and at least a portion of unburnt excess propellant present in the first burnt gas. The second burnt gas from the second combustion flows through a second heat exchanger to transfer heat to the fluid. Burnt gas from each combustion flows in respective burnt gas tubes within a common overall heat exchanger including the heat exchange units, the gas transferring heat to the fluid, the fluid flowing between the burnt gas tubes.
DISPOSITIF D'ECHAUFFEMENT D'UN FLUIDE
17.06.2016
Patent
Elektronische Ressource
Französisch
IPC: | F23C METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN AIR , Verfahren oder Vorrichtungen zur Verbrennung flüssiger oder in Luft verteilter fester Brennstoffe / B64G Raumfahrt , COSMONAUTICS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / F23D Brenner , BURNERS / F28D Wärmetauscher, soweit in keiner anderen Unterklasse vorgesehen, in denen die Wärmetauschmittel nicht in direkte Berührung miteinander kommen , HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT |
Europäisches Patentamt | 2024
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