Quasi-One-Dimensional Multimodes Analysis for Dual-Mode Scramjet

Abstract

A quasi-one-dimensional analytical method with a novel model for precombustion shock train has been proposed to model different modes in the dual-mode scramjet flowfield. The interaction between shock and combustion is modeled by a strength-adaptable model in the isolator, named the "X shock." An iterative procedure is implemented to solve the precombustion shock and the flow properties downstream. The calculation of the combustor is based on a series of governing equations where the effects of area change, friction, and mass injection are included. The release of energy is obtained from a fuel-mixing model or pregiven heat release distributions estimated from experimental results. The numerical results of pressure are compared with the experimental data for validation of the present model. The results show that the quasi-one-dimesional method can be applied to analyze diverse modes in the whole process of the dualmode scramjet combustor. Subscripts in = conditions in the inlet of the isolator max = maximum value min = minimum value 0 = total or stagnation conditions

Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions

“…The analytical method adopted in the present work tends to overcome the shortcomings of previous analytical models by proposing an X-shock model as a strength-adaptable isolator model and combining it with the quasi-1D combustor flow calculation (ODEs) through matching combustion back pressure automatically [12]. It was validated by a series of experimental data [13] and can be applied as a tool to analyze the engine performance in different combustion modes.…”

“…A modified quasi-1D analytical method proposed by the authors [12] has been adopted in this work. First, it is based on aerodynamic quasi-one-dimensional conservation equations of mass, momentum, and energy as well as the equation of state andthe Mach number definition equation.…”

“…The length of the precombustion shock train is obtained through Fig. 5 Sketch of the dual-mode scramjet engine and "X-shock" model [12] experimental semi-empirical equations as described in Billig's milestone work [20]. The interactive process between X-shock and quasi-1D models guarantees the ability of the present method to calculate the whole dual-mode combustion process, ranging from supersonic combustion mode, to dual-mode, and then to subsonic combustion mode.…”

“…Instead of pre-given inlet parameters, the current work includes a simplified 2D inlet model to generate different inlet conditions. Aiming at the maximum net thrust, the simulated annealing algorithm is adopted to optimize the thrust result, which is obtained from the modified quasi-1D analytical model developed by the authors [12]. An optimal combustion mode and inlet condition has been finally chosen for the given flight condition.…”

Numerical Investigation on Flame Stabilization in DLR Hydrogen Supersonic Combustor with Strut Injection

“…Consequently, the quasi-1D analysis, which requires the experimentally measured static wall pressure and a heat release model for problem closure, has been always used to model supersonic combustor as a fast and qualitatively reliable tool (Heiser and Pratt, 1994;Tian et al, 2014). In this regard, the present analysis of a chemical reactions mechanism takes the heat release into account as an important measure.…”