FIELD: engines and pumps.
SUBSTANCE: chamber of a liquid-propellant engine comprises a mixer head with nozzles. Nozzles comprise several coaxially installed bushings that form circular cavities to supply gaseous fuel and liquid oxidant, connecting units of fuel components supply with the combustion chamber cavity and installed along concentric circumferences. The chamber also comprises a shaped regeneratively cooled cylindrical part with a critical cross section and a nozzle. Circular cavities of components supply at the side of the combustion chamber cavity are closed with spacers, where holes are made to supply fuel components to the combustion area. At the side opposite to the combustion zone the specified cavities are closed with a shaped bottom, the inner surface of which is made as stepped, at the same time in the bottom there are radial and axial channels that connect cavities of fuel components supply with appropriate circular cavities.
EFFECT: invention provides for maximum possible completeness of combustion of various types of fuels at low quantity of mixer elements on a nozzle head of a chamber.
3 dwg
Title | Year | Author | Number |
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LIQUID-PROPELLANT ENGINE | 2011 |
|
RU2445496C1 |
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LIQUID-PROPELLANT ENGINE CHAMBER | 2012 |
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LIQUID PROPELLANT ROCKET ENGINE | 2011 |
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Authors
Dates
2012-04-27—Published
2011-03-24—Filed