Numerical study of key parameters for improving cooling efficiency in a regenerative cooled nozzle

Abstract

We have known since the development of the liquid rocket engine began, there was a need to predict maximum heat flow and its problems it affects the engine material, which reduces its efficiency and thus controls the thermal behaviour of the rocket engine wall. to prevent Due to thermal failure, the engine is generally cooled by coolant flowing into the passages that line and pass through the ducts, the hottest part of the engine (i.e. the combustion chamber and the nozzle wall). This is a liquid cooling system. If the refrigerant is a propellant that, once it has passed through the refrigerant circuit, can be injected into Combustion chamber or can be thrown into the sea. The first case is referred to as regenerative cooling system while the latter as a vacuum cooling system. In the case of a high-performance rocket engine (eg as engines LO2 / hydrogen and LO2 / methane) the working pressure of the coolant is supercritical and therefore It behaves far from an ideal liquid or gas. Liquid cooling system (often referred to as regenerative cooling Due to the limited application of vacuum cooling (vacuum cooling) of cryogenic rocket engines and there are several hypotheses in order to prevent the rocket engine from melting and bypass the problem, the technology The background of this master's thesis.