FIELD: engines and pumps.
SUBSTANCE: liquid-propellant engine comprises gas generator turbo compressor unit, chamber with mixing head cooled in regeneration mode and including oxidiser feed unit, fuel feed unit, fire bottom, starting fuel feed channel with outlet chamber composed of hollow shape sleeve. Atomisers are arranged at mixing head units in concentric circles to communicate unit chambers with combustion chamber. Starting fuel feed channel outlet accommodated coaxial hollow spring-loaded axial-displacement sleeve with sealing surface made at its channel inlet. In on position, said extra sleeve interacts with outlet with mating shaped surface on fire bottom inner surface. In another position, its inlet sealing surface interacts with mating sealing element arranged in starting fuel channel.
EFFECT: higher and reliability of ignition system.
5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| LIQUID PROPELLANT ROCKET ENGINE | 2012 |
|
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| LIQUID-PROPELLANT ROCKET ENGINE MIXING CHAMBER | 2012 |
|
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| METHOD OF FEEDING FUEL COMPONENTS INTO LIQUID-PROPELLANT ROCKET ENGINE CHAMBER | 2012 |
|
RU2485340C1 |
| LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER | 2012 |
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RU2485338C1 |
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| IGNITION DEVICE FOR LOW-THRUST ROCKET ENGINES ON NON-SELF-IGNITING GASEOUS (LIQUID) FUEL AND GASEOUS OXIDIZER | 2020 |
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RU2778416C2 |
