Eventos Anais de eventos
ENCIT 2018
Brazilian Congress of Thermal Sciences and Engineering
DESIGN OF THE GENERIC SCRAMJET COMBUSTION CHAMBER
Submission Author:
Ramon Carneiro , RN
Co-Authors:
Paulo Toro, Ramon Carneiro, Jonatha Wallace da Silva Araújo, George Marinho, Gilvan Borba, João Felipe De Araujo Martos, Israel Rêgo
Presenter: Jonatha Wallace da Silva Araújo
doi://10.26678/ABCM.ENCIT2018.CIT18-0056
Abstract
A generic hypersonic airbreathing propulsion based on supersonic combustion ramjet (scramjet) technology has been designed, at the Universidade Federal do Rio Grande do Norte (UFRN), using analytical theoretical analysis (engineering approach). A full-scale generic scramjet model configuration is based on the technological demonstrator scramjet 14-X S, in development at the Instituto de Estudos Avançados (IEAv). A two-dimensional hydrogen powered generic scramjet has been designed 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. In this preliminary design, one-dimensional compressible flow with heat addition and one-dimensional expansion wave (Prandtl-Meyer) coupled to the area ratio theories, may describe many features of the combustor and expansion sections, respectively, of the airbreathing engine. Both theories are used to estimate the thermodynamic properties and the velocities (Mach numbers) of the supersonic atmospheric air flow. 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. Also, the inlet air mass flow and the hydrogen mass flow rates are critical design parameters to burn stoichiometric the hydrogen and the supersonic air in the combustion chamber and generating the high flow velocity at the trailing-edge of the generic scramjet to produce thrust.
Keywords
Scramjet, supersonic combustion, hypersonic airbreathing propulsion
