Scramjet Design for Investigation on Supersonic Combustion with Laser Energy Addition
Felipe Jean da Costa1; Tiago Cavalcanti Rolim2; Ronaldo de Lima Cardoso1; Gustavo Jean da Costa3; Israel da Silveira Rêgo2; Marco Antônio Sala Minucci2; Antônio Carlos de Oliveira2; Paulo Gilberto de Paula Toro2
1 ITA - Instituto Tecnológico de Aeronáutica; 2 IEAv - Instituto de Estudos Avançados; 3 FATEC - Faculdade de Tecnologia de São José dos Campos - Prof. Jessen Vidal
doi:10.20906/CPS/CON-2016-0748
Resumo
Laser energy addition in supersonic combustion has been investigated, in the Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics, in order to reduce the drag, to promote supersonic air mixing with fuel, to improve combustion efficiency and to reduce the ignition time (and consequently combustor length), and acting as a flame holder. This paper presents a methodology to design a scramjet model (inlet-combustor) for laser energy addition in supersonic combustion for experimental investigation at the Hypersonic Shock Tunnel T3. In the aerodynamic design of scramjet with one compression ramp, flying at 30 km altitude with Mach number 7, one may considered the following steps: i) air flow with perfect gas behavior, inviscid (no boundary layer), and mass flow captured by the scramjet inlet will pass through the scramjet engine combustor (so that the incident shock wave of the compression system focuses in the cowl leading edge (shock-on-lip) and the reflected shock wave focuses at the combustion chamber entry (shock-on-corner), ii) boundary layer (viscous effects); iii) interaction boundary-layer-shock wave between the compression ramps in the lower surface; iv) real gas effects; v) fuel injection; and vi) combustor design at constant area. It should be noted that the methodologies addressed obey the fundamental principles of physics with respect to the Mass, Linear Momentum and Energy. The quantification of the fundamental principles of physics is carried out through the Navier-Stokes Equations, which are valid, a priori, to continuous medium (altitudes up to 100 km). In general, Navier-Stokes Equations may applied for transient flow; incompressible or compressible; laminar and turbulent; neglecting field forces, volumetric heating and mass diffusion. Finally, oblique shock wave theory and one-dimensional flow with friction theory, which are based on the Navier-Stokes Equations, may be applied at the inlet and combustor sections of the scramjet experimental model. Fuel injection will be considere
Palavras-chave: scramjet; Hypersonics; Laser Energy Addition; Supersonic Combustion