Fixed geometry rocket thrust chamber with variable expansion rat

Details Fixed geometry rocket thrust chamber with variable expansion rat Fixed geometry rocket thrust chamber with variable expansion rat

1985-08-02

1987-02-24

Croyle, Carlton R.

Power plants

Reaction motor

Liquid oxidizer

60741, F02K 900, F02K 942, F02K 972

Patent

active

046447458

ABSTRACT:
The present invention provides a rocket thrust chamber (30) comprising a combustor (32) with a fixed divergent profile, a nozzle (36) for further expanding the output of the divergent combustor and a high-velocity, throttleable injector (34) for injecting propellants at such an initial velocity and initially rapid, axial burning rate that the injected propellants achieve sonic flow conditions at preselected locations within the divergent combustor according to throttle setting. In operation, the throttle setting fixes the location of the sonic flow line within the divergent combustor, and the ratio of the nozzle exit area with respect to the effective area of the divergent combustor at the sonic location area fixes the expansion ratio for that throttle setting. At launch, the engine delivers a high propellant flow rate and a moderate expansion ratio, while in space, it delivers a low propellant flow rate and a far greater expansion ratio.

REFERENCES:
patent: 2995008 (1961-08-01), Fox
patent: 3112988 (1963-12-01), Coldren et al.
patent: 3321920 (1967-05-01), Walter et al.
patent: 3451221 (1969-06-01), Boe
patent: 3507116 (1970-04-01), Berry
patent: 3527056 (1970-09-01), Hoffman
patent: 3717999 (1973-02-01), Wilson
Gill et al., "Determination of Rocket Motor Combustion Parameters by Means of a Diverging Reactor"; 7th Combustion Symposium, 1958.
Lieamann et al., Elements of Gas Dynamics, Wiley & Sons, New York, 1967, pp. 301-303.

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