OPTIMIZATION OF LIQUID ROCKET ENGINE
Analyzes possible options for circuit design of oxygen-methane rocket engine with a reducing gas generator. The estimate was used as criterion of optimization of the gas temperature in the turbine. The questions of proof-of-concept reusable liquid rocket engine propellant components oxygen - liquefied natural gas, which uses a turbopump unit with two turbines on the same shaft, one of which runs on gas with excess oxygen and the second is gasified in the cooling fuel path. Made experimental model, carried out fire tests and received its main technical characteristics. The concept of main reusable liquid rocket engine propellant components oxygen - liquefied natural gas (methane), which uses a turbopump unit with two turbines on the same shaft, one of which runs on gas with excess oxygen and the second is gasified in the cooling path of the fuel chamber. Presentations conducted hot fire tests of the experimental setup and obtained its main technical characteristics. Given the promising full-size layout scheme liquid-propellant rocket engines thrust 390 and 1960 kN.