Power plants – Reaction motor – Liquid oxidizer
Patent
1988-03-24
1989-11-28
Casaregola, Louis J.
Power plants
Reaction motor
Liquid oxidizer
60265, F02K 942
Patent
active
048829048
ABSTRACT:
A method for operating a rocket engine by injecting fuel and oxidizer into an elongated combustion chamber in two flows, a core flow where the fuel and oxidizer are intimately mixed and immediately combusted and a peripheral curtain flow which surrounds the core flow and which is in contact with the combustion chamber wall to cool it and limit the heat transfer from the wall to the injector to prevent vapor locks in the injector. To prevent decomposed or partially combusted propellant products from chemically reacting with the chamber wall no mixing of fuel and oxidizer takes place in the curtain flow. The curtain flow is deflected radially inward into the core flow, before decomposed or partially combusted products can come into contact with the wall, into the core flow to fully combust the curtain flow out of contact with the wall. The rocket engine is defined by serially arranged first and second combustion chambers and an injector constructed to from the core and curtain flows. A ring plate projects radially inward at the downstream end of the first chamber and deflects the curtain flow into the coreflow.
REFERENCES:
patent: 2523656 (1950-09-01), Goddard
patent: 3254485 (1966-06-01), Bernstein
patent: 3303654 (1967-02-01), Bringer
patent: 3354651 (1967-11-01), Novotny
patent: 3712059 (1973-01-01), Drexhage
Aerojet-General Corporation
Casaregola Louis J.
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