Влияние механизма воспламенения топлива искрой и нагретой поверхностью на запуск кислородноводородного ракетного двигателя малой тяги

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Влияние механизма воспламенения топлива искрой и нагретой поверхностью…
ISSN 0236-3941. Вестник МГТУ им. Н.Э. Баумана. Сер. Машиностроение. 2017. № 3 39
SPARK AND HEATED SURFACE IGNITION MECHANISM EFFECT
ON LAUNCH OF THE OXYGEN-HYDROGEN THRUSTER
A.V. Kochanov
A.G. Klimenko
S.G. Rebrov
M.V. Keldysh Research Centre, Moscow, Russian Federation
Abstract Keywords
The study gives the results of research into fuel ignition in
the chamber and launch of the thruster operating on
gaseous oxygen and hydrogen. We examined the electric
spark, laser and hot-tube ignition systems with an igniter
in the pre-combustion chamber. We carried out the tests
with the engine running in the single-shot and pulse
modes with the initial vacuum in the low-pressure cham-
ber. We applied the hot-tube method to determine the
influence of the residual pressure in the low-pressure
chamber with the engine's intensive impulse operation on
the fuel ignition. The experiments show that with electric
spark and laser methods, the fuel ignition can occur both
in the pre-combustion chamber when both components
of the fuel enter it, and downstream from the energy
input zone due to the movement of ionized gas to the
region with a ignition-favorable concentration of the fuel
mixture
Thruster, ignition, glow plug, oxygen,
hydrogen, combustion chamber, pre-
combustion chamber
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