U.S. Patent Specifications

Abstract

In propulsion apparatus having a combustion chamber with an open‐discharge nozzle at its outer end, in combination, a substantially spherical chamber wall for said combustion chamber and having an axial feed opening at its inner end, an inner casing enclosing an inner jacket space about said spherical wall, an outer casing enclosing an outer jacket space about said inner casing, and means to supply a liquid oxidizer under pressure to said outer jacket space, said inner jacket casing having spaced openings through which portions of said liquid arc sprayed against the combustion chamber wall, said inner jacket space communicating with an inner opening at its inner end, which opening is formed between adjacent portions of said combustion chamber wall and said inner casing, and through which annular opening partially vaporized oxidizer is fed from said inner jacket space to said combustion chamber, and means to supply liquid fuel to said combustion chamber in a direction opposed to the path of travel of the oxidizer.

Citation

(1956), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 28 No. 12, pp. 438-438. https://doi.org/10.1108/eb032779