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
2016-06-17
Patent
Electronic Resource
French
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 |
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