Liquid propellant rocket engine with parallel auxiliary flow, an

Details Liquid propellant rocket engine with parallel auxiliary flow, an Liquid propellant rocket engine with parallel auxiliary flow, an

1993-12-09

1995-04-11

Bertsch, Richard A.

Power plants

Reaction motor

Liquid oxidizer

60258, 60259, F02K 900, F02K 942, F02K 972

Patent

active

054047153

ABSTRACT:
The rocket engine is fitted with an injection device comprising a single injection plate having a central portion that defines the end of the burn zone of the combustion chamber and that contains first propellant injectors having a high mixing ratio adapted to the conditions under which hot gases are produced in the burn zone, and a peripheral portion in the form of a ring that defines the end of an annular cavity of a gas generator and that contain second propellant injectors having a low mixing ratio and adapted to the conditions under which hot gases are produced in the gas generator. The gas generator is thus integral with the combustion chamber and the annular cavity of the gas generator is separated from the burn zone of the combustion chamber by a cylindrical wall that extends axially perpendicularly to the injection plate and that is fixed thereto in sealed manner.

REFERENCES:
patent: 3036428 (1962-05-01), Chillson
patent: 3286469 (1966-11-01), Artherton
patent: 3413810 (1968-12-01), Kaufmann
patent: 3553964 (1971-01-01), Kircher, III

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