Arrangement for the production of rotational energy in rocket co

Details Arrangement for the production of rotational energy in rocket co Arrangement for the production of rotational energy in rocket co

1973-12-10

1976-02-10

Feinberg, Samuel

Power plants

Combustion products used as motive fluid

Combustion products generator

60 3974S, F02G 100

Patent

active

039370127

ABSTRACT:
An arrangement for producing rotational energy, particularly for generating thrust gases in rocket combustion chambers using hypergolically reacting propellants, comprises a rocket combustion chamber having a closed end and a gas discharge end with an impeller mounted in the closed end. The impeller has a plurality of spaced vanes which extend radially and which define flow ducts therebetween having discharge ends which extend substantially tangential to the combustion periphery. The apparatus includes means for directing hypergolically reacting propellant components into the combustion chamber at a location in which they are deposited at the inner radial ends of the flow ducts. The oxygen carrier propellant is supplied radially inside of the other propellant component so that it forms a cooling veil along the impeller. The impeller is advantageously rotatably mounted so that the components are whirled outwardly into the combustion chamber and the individual blades are provided with passages in order to enhance the interreaction of the propellant components.

REFERENCES:
patent: 2395403 (1946-02-01), Goddard
patent: 2602290 (1952-07-01), Goddard
patent: 3036428 (1962-05-01), Chillson
patent: 3169368 (1965-02-01), Munding
patent: 3568445 (1971-03-01), Munding et al.
patent: 3717999 (1973-02-01), Wilson

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