Rocket engine burner with porous metal injector for throttling o

Details Rocket engine burner with porous metal injector for throttling o Rocket engine burner with porous metal injector for throttling o

1995-08-22

1999-01-12

Freay, Charles G.

Power plants

Reaction motor

Liquid oxidizer

60 39465, 60 3906, 2394245, 431 11, 431243, F02K 900

Patent

active

058573232

ABSTRACT:
A rocket engine burner for throttling over a large thrust range from full thrust to very low thrust. The rocket engine burner comprises a propellant injector assembly, a combustion chamber, and an ignitor. The propellant injector assembly comprises one or more hollow injectors and a secondary propellant manifold in communication with the hollow injectors to provide them with a secondary propellant. The propellant injector assembly also includes a primary propellant manifold and a porous injector that extends across the inlet of the combustion chamber and is in communication with the primary propellant manifold to receive the primary propellant. The primary propellant flows through the porous injector and is injected into the combustion chamber. The porous injector has one or more openings through it which receive the hollow injectors. The secondary propellant flows through the hollow injectors and is injected into the combustion chamber. The ignitor is in communication with the combustion chamber to ignite the injected primary and secondary propellants to produce combustion products that exit the outlet of the combustion chamber.

REFERENCES:
patent: 3446023 (1969-05-01), Mosier
patent: 3581495 (1971-06-01), Kah
patent: 4478045 (1984-10-01), Shekleton
patent: 4936091 (1990-06-01), Schoenman
"Porous Metals for High Performance", Mechanical Engineering, vol. 16 (6) :32, (1994).

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