FIELD: engines and pumps.
SUBSTANCE: method for supplying fuel components to liquid-propellant engine chamber involves the oxidiser supply through central channel of hollow tip of coaxial spray injector and fuel supply through annular gap between hollow tip and sleeve of the above injector. On hollow tip there located are pylons interacting with inner surface of the sleeve and aligning the tip relative to the sleeve. Some part of oxidiser flow is supplied through channels which are made in pylons; at that, one end of the above channels opens to the tip cavity and the other one - to sleeve cavity; discharge nozzle is installed in outlet part of hollow tip with possibility of being replaced.
EFFECT: invention provides combustion efficiency of fuel components.
2 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| LIQUID-PROPELLANT ROCKET ENGINE MIXING HEAD | 2011 |
|
RU2451200C1 |
| LIQUID-PROPELLANT ENGINE CHAMBER | 2011 |
|
RU2445494C1 |
| LIQUID-PROPELLANT ENGINE | 2011 |
|
RU2445498C1 |
| COAXIAL SPRAY INJECTOR | 2011 |
|
RU2445497C1 |
| LIQUID-PROPELLANT ENGINE | 2011 |
|
RU2445500C1 |
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RU2490500C1 |
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RU2501967C1 |
| METHOD OF FUEL COMPONENTS FEED IN THREE-COMPONENT LIQUID PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER | 2012 |
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RU2502886C1 |
