Расчет температур стенок жаровой трубы камеры сгорания прямоточного воздушно-реактивного двигателя при завесном охлаждении

Abstract

Along with the turbojet engines, cruise missiles are using the ramjet engines, Features of the ramjet rockets use in most cases are characterized with the combustion chamber operating for significant time at the maximum heating, which makes it a rather heat-loaded unit that requires solving complex issues of the heat resistance. Therefore, calculations are relevant to determine thermal state of the combustion chamber elements, which makes the basis for making rational design decisions. This paper determines temperatures of the burner liner wall of the ramjet engine main combustion chamber affected by combustion products and cooling air. Certain similarity in the design of the burner liners of turbojet and ramjet engine on liquid fuel made it possible to adapt calculation methods worked out for a turbojet engine to the ramjet engine combustion chambers. Main sections of the combustion chamber and their characteristic features were identified. A system of non-linear heat transfer equations was solved using empirical coefficients for both cooled and uncooled sections. Graphs of temperature distribution in sections of the burner liner along the entire length of the combustion chamber were plotted. Qualitative analysis of the obtained results showed that the applied method could be used to determine the thermal state of the burner liner walls as the first approximation, without taking into account local design features, but using only the aerial vehicle flight conditions and the liquid fuel parameters.