Ablative baffle for a liquid rocket engine thrust chamber

Details Ablative baffle for a liquid rocket engine thrust chamber Ablative baffle for a liquid rocket engine thrust chamber

2006-05-02

2006-05-02

Kim, Ted (Department: 3746)

Power plants

Reaction motor

Liquid oxidizer

Reexamination Certificate

active

07036303

ABSTRACT:
An ablative baffle for a liquid rocket engine thrust chamber that includes a hub member having a hollow structure, of which both top and bottom parts are open; a plurality of blade rib members, each of which is connected removably at one end to the outer surface of the hub member; and a blade-connecting member having a hollow structure, of which both top and bottom parts are open, to the inner part of which each of blade rib members is connected at the other end. An ablation cooling method is utilized which includes the composite heat resistant material structure with metal core, so that a liquid rocket engine system may be simplified, and the reliability of liquid rocket engine increases, and the manufacturing cost is cut down.

REFERENCES:
patent: 2884859 (1959-05-01), Alexander et al.
patent: 3242670 (1966-03-01), Buswell
patent: 3479819 (1969-11-01), Bogue
patent: 3545203 (1970-12-01), Rumbold
patent: 3742701 (1973-07-01), Feemster et al.
patent: 3790088 (1974-02-01), Wilson
patent: 6352030 (2002-03-01), Doll et al.
“Liquid Rocket Engine Combustion Stabilization Devices,” National Aeronautics and Space Administration, NASA Space Vehicle Design Criteria (Chemical Propulsion), Nov. 1974, pp. 9-35.

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