Eventos Anais de eventos
ENCIT 2018
Brazilian Congress of Thermal Sciences and Engineering
DESIGN AND ANALYSIS OF A GENERIC SCRAMJET AIR INLET
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.CIT18-0751
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 inlet 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 (shock wave) theory, which may readily describe many features of compression region of the airbreathing engine, is used to estimate the shock wave angles, thermodynamic properties and the velocities (Mach number) of the hypersonic atmospheric air flow, at the generic scramjet inlet. 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. The turning (deflection) angles of the compression section ramps are optimized by using the same total pressure (recovery) ratios across each incident oblique shockwave. Additionally, calculations are done in order to check if the momentum and the energy are conserved across each oblique shockwave. Finally, based on the mass conservation law, and the control volume (that involve the scramjet air capture area and the combustion chamber), it is estimate the height of the combustion chamber of the present generic scramjet to flight coupled with the Brazilian hypersonic accelerator vehicle, which is composed by two-stage solid rocket engines to accelerate the generic scramjet to the altitude of 30 km in velocity corresponding to the Mach number 6.8.
Keywords
Scramjet, supersonic combustion, hypersonic airbreathing propulsion
