Обеспечение надежного охлаждения камеры сгорания кислородно-водородного жидкостного ракетного двигателя первой ступени ракеты-носителя при глубоком дросселировании тяги

Abstract

The purpose of the paper was to analyze the possibility of deep throttling of a liquid rocket engine under reliable cooling of the chamber. Within the study, we solved a scientific and technical problem, developed a limiting cooling scheme, which is the scientific novelty of this research. To estimate the cooling, we used the HOLOD software package developed at Bauman Moscow State Technical University. To determine the radiant heat flux, we applied the Stefan-Boltzmann law. Findings of the research show that the engine thrust can be throttled up to 28% of the nominal rating. At this value, we ensured the maximum possible cooling of the chamber walls without burnout. It was possible to obtain the value due to the cooling scheme for the chamber, which implies the separation of the coolant flows and the use of a loop solution at the nozzle section. For reliable cooling, the coolant was supplied at the most heat-stressed section of the chamber.