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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

klimenkokerc@mail.ru

S.G. Rebrov

rebrov_sergey@mail.ru

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

REFERENCES

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live (varianty) [Propulsion chamber of the thruster working on binary non-self-igniting gas

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[Herald of the Bauman Moscow State Tech. Univ., Mechan. Eng.], 2015, no. 2,

pp. 57–67 (in Russ.). DOI: 10.18698/0236-3941-2015-2-57-67

Available at:

http://vestnikmach.ru/catalog/avroc/pplan/752.html

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, 2012, no. 57 (in Russ.).

Available at:

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