FIELD: engines and pumps.
SUBSTANCE: invention relates to liquid propellant jet engines. Liquid propellant jet engine contains combustion engine with cooling loop, oxidiser pump, fuel pump, two separate turbines. According to invention combustion chamber cooling loop is made of two separate areas. Note that the input of one of these areas is connected to the output of the oxidiser pump and its output is connected to one of the turbines input. The input of the other cooling channel area is connected to the output of fuel pump and its output is connected to the other turbine input.
EFFECT: invention provides decrease of engine component tension level and structure simplification.
1 dwg
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