Diseño conceptual y preliminar de un motor estatorreactor de combustión supersónica para vehículos de propulsión hipersónica

Abstract

This paper develops a historic revision of Supersonic Combustion Ramjet engines, which are called Scramjet, a state of art of the most significant advances in this new technology, in order to identify the achievements and advantages, that they have in the aerospace industry. A theoretical review is made to determine design parameters of a scramjet engine with ignition at higher speed Mach 5 and altitude of 95,000 ft (28,956 km), is realized an analysis of the fuel selection for use with determine characteristics. Subsequently is designed analytically the basic components of a Scramjet engine implementing a supersonic combustion system, this engine are distributed in three principal devices intake, combustion chamber and nozzle. He has a basic principle of operation that is free of moving parts in his basic cycle and the internal geometry can be compared with a empty duct that is crossed for air mixed with-fuel, by maintaining the flow at supersonic speeds through the entire combustion process (hence its name) and finally the Scramjet engine provide the hypersonic velocity to respective boosted vehicle. to achieve the ignition of the mixture air-fuel is necessary flow at speeds higher than 5 Mach in the intake and remain supersonic in the combustion chamber, finally the flow is expelled theoretically can be achieve hypersonic velocities between 12 Mach and 24 Mach. Due the poor knowledge and hard access to the scientific information about these engines in Colombia, the goal of these investigation project is describe conceptually and preliminary the design parameters, geometric configuration, systems distribution and select the fuel according to the engine needs, specifically pure Scramjet engine with ignition higher at 5 Mach . Finally simulate the scramjet operation in computational fluid dynamics or CFD.