FIELD: engines and pumps.
SUBSTANCE: liquid-propellant engine includes chamber with mixing head in which there located are injectors consisting of several coaxially installed sleeves forming annular cavities for supply of gaseous fuel and liquid oxidiser, which are installed in mixing head along concentric circles and connect the cavities of the units to the combustion chamber cavity. Engine includes at least one gas generator, at least one turbo-pump unit and feed and control units. Annular cavities for supply of fuel components on the side of combustion chamber cavity are covered with spacer plates in which there made are holes for supply of fuel components to combustion zone, and on the side opposite to combustion zone the above cavities are covered with shaped bottom the inner surface of which is stepped. At the bottom there made are radial and axial channels connecting the fuel component supply cavities to the appropriate annular cavities.
EFFECT: higher combustion efficiency of fuels of various types at smaller number of mixing elements on injector head of the chamber of liquid-propellant engine.
3 dwg
Title | Year | Author | Number |
---|---|---|---|
LIQUID PROPELLANT ROCKET ENGINE | 2011 |
|
RU2450155C1 |
LIQUID PROPELLANT ROCKET ENGINE | 2012 |
|
RU2493411C1 |
LIQUID PROPELLANT ROCKET | 2012 |
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RU2497010C1 |
LIQUID PROPELLANT ENGINE | 2012 |
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RU2496021C1 |
LIQUID PROPELLANT ENGINE | 2012 |
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RU2494274C1 |
LIQUID-PROPELLANT ENGINE | 2012 |
|
RU2490506C1 |
LIQUID-PROPELLANT ENGINE | 2011 |
|
RU2445498C1 |
LIQUID-PROPELLANT ENGINE | 2012 |
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RU2490507C1 |
LIQUID PROPELLANT ROCKET ENGINE | 2012 |
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RU2493410C1 |
LIQUID PROPELLANT ROCKET ENGINE | 2012 |
|
RU2493406C1 |
Authors
Dates
2012-03-20—Published
2011-03-24—Filed