CRYOGENIC-LIQUID-PROPELLANT ROCKET ENGINE

摘要

FIELD: space vehicles and missile-carrier accelerating units using cryogenic oxidizer (liquid oxygen or hydrocarbon fuel. SUBSTANCE: engine has combustion chamber 1 with nozzle 3, turbine-driven oxidizer pumps 7 for hydrocarbon fuel 9 with flow lines 12, 13 connected to drive turbines 10, 14, and gas generator 11 with cooling jacket 15. Gas generator inlet is connected to oxidizer and fuel flow lines; inlet of cooling jacket is connected to fuel flow main line. Combustion chamber has cooling channel 4 communicating with outlet of gas generator cooling jacket which connects it to combustion-chamber mixing head 2; main flow of hydrocarbon fuel passed through gas-generator cooling jacket cools down generator gas to temperature ensuring desired thermal stability of turbine blades during combustion of fuel with optimal proportion of components in gas generator. EFFECT: improved economic efficiency of engine. 1 dwgi