Injection element of coaxial design for rocket combustion engine

Details Injection element of coaxial design for rocket combustion engine Injection element of coaxial design for rocket combustion engine

1996-04-26

1998-01-06

Kashnikow, Andres

Fluid sprinkling, spraying, and diffusing

Combining of separately supplied fluids

Including whirler device to induce fluid rotation

2394245, 239429, 239433, 60258, B05B 704, B05B 706, F02K 900, F02K 942

Patent

active

057045518

ABSTRACT:
Injection element of coaxial design for rocket combustion engines and for operation with two propellants, at least one of which disintegrates into drops with difficulty only, comprising a central body for the more readily disintegrating propellant (oxidant), whose flow channel generates a conical drop distribution at the outlet; a sleeve concentrically surrounding the central body to form an annular flow channel for the less readily disintegrating propellant (fuel); and a flow splitter which splits this propellant flow into a plurality of individual flows. The flow splitter has an even number of passage channels, which are uniformly distributed around the central body and cooperate in pairs in terms of an impact atomization ("impinging"), wherein the axes of two adjacent passage channels each intersect downstream of the flow splitter and upstream of their points of impact on the propellant cone discharged from the central body.

REFERENCES:
patent: 3468487 (1969-09-01), Warren
patent: 5072883 (1991-12-01), Vidusek
patent: 5456065 (1995-10-01), Dargies

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