Thrust nozzle for rocket engine with ablating lining

Details Thrust nozzle for rocket engine with ablating lining Thrust nozzle for rocket engine with ablating lining

1980-11-26

1983-05-24

Croyle, Carlton R.

Power plants

Reaction motor

Motive fluid from diverse generators alternatively ejected...

60909, 60251, 60271, 23926515, F02K 972, F02K 997

Patent

active

043844545

ABSTRACT:
A thrust nozzle for a reaction engine having a combustion chamber with a sustained flight discharge nozzle defined therein for the passage of thrust gases and a sustained flight thrust arrangement connected to the combustion chamber for supplying thrust gases through the combustion chamber, the thrust nozzle comprising a starting nozzle formed on an interior wall of the combustion chamber radially inwardly of the sustained flight discharge nozzle made of a plurality of layers of ablatable material which are ablated by the passing thrust gases to discharge vaporized or fragmentary parts of the layers of ablatable material.

REFERENCES:
patent: 3073111 (1963-01-01), Hasbrouck
patent: 3250070 (1966-05-01), Milewski et al.
patent: 3633631 (1972-01-01), Hatch et al.
patent: 3776466 (1973-12-01), Ray

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