Abstract—There is a gap at combustor-turbine interface where leakage flow comes out to prevent hot gas ingestion into the gas turbine nozzle platform. The leakage flow protects the nozzle endwall surface from the hot gas coming from combustor exit. For controlling flow’s stream, the gap’s geometry is transformed by changing fillet radius size. During the operation, step configuration is occurre...

In this paper we report a new development on the numerical model for aluminum-steam combustion. This model is based on diffusion flame of continuum regime and the thermal equilibrium between the particle and the flow field, which can be used to calculate the aluminum particle combustion model for two phase calculation conditions. The model prediction is in good agreement with the experimental d...

This work performs an analysis of plasma-assisted non-premixed H2-air flames in Y-shaped micro combustors the presence field emission dielectric barrier discharge (FE-DBD) plasma actuators. The combustion, flow, and heat transfer characteristics are numerically investigated, effect sinusoidal discharges on combustion performance is examined at various equivalence ratios (φ). A coupled chemical ...

Airbreathing rotating detonation wave engine cycle analysis" a r t i c l e i n f o a b s t r a c t A cycle analysis model for an airbreathing, rotating detonation wave engine (RDE) is presented. The engine consists of a steady inlet system with an isolator which delivers air into an annular combustor. A detonation wave continuously rotates around the combustor with side relief as the flow expan...

A well-designed CFB combustor can burn coal with high efficiency and within acceptable levels of gaseous emission. In this study, the combustion efficiency of CFB combustor based on the losses has been defined and effects of operational parameters on combustion efficiency have been investigated by a dynamic 2D model which has been developed in our previous studies. Investigations on combustion ...

A theoretical study analyzing three-dimensional combustion acoustic instabilities in a liquid propellant rocket engine combustor has been conducted. A linear theory based on Crocco’s pressure sensitive time lag model is used. To apply this theory the combustor is divided into two main components, including the combustion chamber and the converging part of the nozzle. The assumption of concentra...