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Desired endpoint of new line (at the "X")

development The stress transport equations are again written in density-weighted form but now additional terms appear for combusting flows which require modelling Of the available models, that described in (11) appears to be one of the most reliable and has produced good results for reacting flow The scalar fluxes must again be modelled and this may be done using the second-moment closure also described in (11) This level of closure allows us to capture effects such as counter-gradient diffusion observed in premixed flames which cannot be represented by lower order closures The Reynolds stress and scalar flux closures described represent the current best practice for application to practical gas turbine combustor calculations, since they balance physical realism with computational economy However, we are still limited by the fundamental assumptions of all Reynolds averaging methods whereby we have characterized the turbulence field by a single length and time scale.

This is likely to be a significant compromise particularly in flows where the effects of solid walls are important, such as the modelling of cooling films or diffuser performance In such cases we may wish to move to a more comprehensive treatment of the turbulence structure that captures at least some of the range of eddy scales and so the energy cascade The only method currently offering promise in this area for engineering flows at high Reynolds number is the Large Eddy Simulation (LES) approach Here, we perform an unsteady calculation on a grid sufficiently fine to resolve the large eddy structures and simulate only those that cannot be resolved on the grid (which should be that part of the flow within the turbulence inertial subrange).

This method is attractive for a number of reasons for calculating the flows in combustion systems: The inherently unsteady nature of the calculation and capture of multiple length and time scales should allow the calculation of structures such as cooling films which are poorly predicted by many Reynolds-averaged techniques The decay of the cooling film is controlled by the rate of mixing between the film and the hot mainstream; this mixing process is governed by large-scale vortex motions in the interface leading to entrainment of hot gas into the film These processes should be more amenable to prediction by LES than by Reynolds-averaged methods which should improve the data that can be supplied to combustor life calculations LES allows us to directly simulate the larger turbulence scales which will be most influenced by the geometry and boundary conditions.