FIELD: rocket science.
SUBSTANCE: invention relates to liquid-propellant engines (LPE) and can be used in their designing. Liquid-propellant engine running on cryogenic components fuel chamber with cooling circuit consisting of two sections of cooling oxidiser and fuel turbo pump units, on the turbine which of the sections are supplied cooling gas-fired and heated propellant components, ACS units, igniters for ignition of fuel components in the "hot units, the output of each section of the cooling circuit is connected with ignition devices.
EFFECT: invention provides higher reliability due to usage of gasified in the cooling channel of combustion chamber fuel components for ignition of fuel components in ignition device of the chamber.
1 cl, 1 dwg
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