Combustion oscillation in a rocket combustor was analyzed using Variational Auto-Encoder (VAE). Dimension reductions were conducted on various physical quantities (p′, ˙q′, etc.) the combustor. Orthogonal modes obtained proper orthogonal decomposition for output of VAE. Pumping and damping regions identified distribution Rayleigh Index each mode. Three characteristic that supply energy to oscil...

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Initiation and stabilization of oblique detonation waves (ODWs) are important to the successful application engines (ODEs), which, however, have been rarely studied under realistic combustor conditions. In this study, flow structures, characteristics potential thrust performance (under different combustor's geometries with ODW reflection locations) in a typical hydrogen-fueled ODE numerically b...

Various kinds of pilot burners were experimentally investigated to examine the effects their geometry and location relative main burner a real size combustor. In addition, wide range fuel equivalence ratios analyze feasibility novel for conventional application. From results, it is shown that with multi air holes had thin, straight, long stable flame, while thick, lifted, short unstable flame. ...

Abstract Online wall temperatures were measured with fiber-coupled phosphor thermometry in a full-scale gas turbine combustor. The combustor was operated natural and up to 100 vol% hydrogen at engine-relevant conditions. Two phosphors tested for this application, namely YAG:Dy YAG:Tm;Li. Although YAG:Tm;Li seemed be the most promising it turned out incompatible used setup due strong interfering...

Three-dimensional n-heptane spray flames in a swirl combustor are investigated by means of direct numerical simulation (DNS) to provide insight into realistic spray evaporation and combustion as well as relevant modeling issues. The variable-density, low-Mach number Navier–Stokes equations are solved using a fully conservative and kinetic energy conserving finite difference scheme in cylindrica...

The present work addresses unsteady flame dynamics in a lean-premixed swirl-stabilized combustor, with attention focused on the transition of flame structure from a stable to an unstable state. It was found that the inlet temperature and equivalence ratio are the two most important variables determining the stability characteristics of the combustor. A slight increase in the inlet mixture tempe...