Eventos Anais de eventos
ENCIT 2018
Brazilian Congress of Thermal Sciences and Engineering
CHEMICAL REACTIONS MODEL APPLIED TO SUPERSONIC COMBUSTION
Submission Author:
David Romanelli Pinto , SP , Brazil
Co-Authors:
Paulo Toro, Eduardo José Cidade Cavalcanti, Matheus Lima, Ítalo Sabino Arrais Bezerra, João Felipe De Araujo Martos, Felipe Jean da Costa, David Romanelli Pinto, Israel Rêgo
Presenter: Ítalo Sabino Arrais Bezerra
doi://10.26678/ABCM.ENCIT2018.CIT18-0181
Abstract
A two-dimensional hydrogen powered generic scramjet inlet has been considering to demonstrate, in atmospheric flight, a supersonic combustion, of atmospheric air (in supersonic speed) with hydrogen, on an acceleration mission to 2050 m/s(Mach number 6.8) at 30 km geometric altitude. Scramjet technology offers substantial advantages to improve performance of aerospace vehicle that flies at hypersonic speeds through the Earth’s atmosphere, by reducing onboard fuel. Basically, scramjet is a fully integrated airbreathing aeronautical engine that uses the oblique/conical shock waves generated during the hypersonic flight, to promote compression and deceleration of freestream atmospheric air at the inlet of the scramjet. Fuel, at least sonic speed, may be injected into the supersonic airflow just downstream of the inlet. Right after, both atmosphere air and on-board hydrogen fuel are mixing. The combination of the high energies of the fuel and the oncoming hypersonic airflow the combustion at supersonic speed starts. The scramjet engine is divided into several components based on key design parameters to assess the engine performance as a function of these parameters. One of the most important design aspects is the temperature at the entrance of the combustion chamber because the compression must provide enough high temperature, higher than ignition temperature of the hydrogen, for supersonic combustion with the supersonic atmospheric air, at the combustion chamber. In this work the conditions after burning hydrogen H2 and air (O2 and N2), at stoichiometric chemical reaction, will be presented.
Keywords
Scramjet, supersonic combustion, hypersonic airbreathing propulsion
