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In order to study spray combustion, an experimental test rig was developed at ONERA to partially characterize the flow conditions inside the combustion chamber of a gas turbine. Experimental campaigns using laser-based diagnostics were performed to provide an experimental database under reacting and non-reacting conditions. The paper first describes the Mie scattering image-processing to detect the droplets in the spray, and to calculate 2D maps of droplet number density and mean inter-droplet distance. The method is subsequently used to investigate the spray behavior under both reacting and non-reacting conditions according to global-averaging and phase-averaging methods. Experimental findings on the spatial droplet distribution in the spray are compared to the simple regular grid distribution and the Hertz-Chandrasekhar distribution. Results show that, under both conditions, there is an affine relationship between the inverse square root of the mean droplet number density and the nearest-neighbor inter-droplet distance. Moreover, observations suggest that the droplet spatial distribution fits more closely to a Hertz-Chandrasekhar distribution than a simple regular grid distribution, which may bring new insight for spray modeling.

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Motivated by the high demand for an alternative, more reliable, high energy ignition source to facilitate the re-ignition of lean-burn combustion chambers which are necessary to reduce pollutant emissions, a new set-up has been designed to study plasma / microwave sources. The use of a waveguide-based resonant cavity leads to very low power plasma ignition. An example in this paper shows that a plasma at atmospheric pressure can be maintained with less than 2 W input power. Such a performance is possible using the large variety of possible adjustments (resonance frequency, different kind of initiators,…) that this versatile set-up offers. To illustrate the wide range of possible studies, another example is given and discussed : Minimum ignition energy for an ethanol droplet stream with aluminum and stainless steel initiators. The results show that the initiator material and its surface quality have an influence on the minimum ignition energy, especially for large gaps. Depending on the gap size we can get down to under 10 W entering the cavity to ignite the droplet stream.

The present study aims at contributing to the development of a methodology to predict and improve the ignition performances of aircraft combustors. A model has been developed to investigate the early growth of a spherical ignition kernel in a two-phase flow mixture. It has been combined with a multiphysic code through two different approaches. The ignition kernel model is used to build the ignition probability map of a combustor. The output of the model can also be introduced as an initial condition in an unsteady simulation to test the flame propagation in the combustor. To validate both methods, RANS and LES simulations have been performed on an experimental combustion chamber, reproducing one sector of an industrial combustor.

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Different experimental and numerical works were conducted at ONERA in order to carry out information about the evaporation of mono and multicomponent droplets. Different models were proposed and tested in computing codes. The goal of this paper is to describe the evaporation of carburant droplets in a highly turbulent and heated flow by numerical simulation. Firstly, the numerical approach is used in the comprehension of the mono and two-phase flow behavior. Secondly, a simple evaporation model implemented in the code CEDRE is tested for this configuration.

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