Simulation aux Grandes Échelles Traitement des parois Perte de chargeLarge-Eddy Simulations (LES) of a swirl experimental burner are performed using a compressible and a low Mach number solver. The investigations are focused on the modeling strategies in LES aimed at validating the flow predictions and principally the associated pressure losses. Accurate prediction of pressure drop through complex geometries, such as those typically encountered in industrial swirlers, is indeed of paramount importance to design and optimize the engine efficiency. LES is here probed and tested to identify the model parameters affecting pressure losses: grid resolution, wall treatment or solver accuracy, with the aim of highlighting the requirements for accurate pressure drop predictions. Results show that for the high Reynolds number flow considered, the wall law model provides the best predictions and minimizes the error compared to experimental findings with a reasonable overall CPU cost.
The design of a gas turbine combustion chamber integrates multiple contradicting objectives. Among all the parameters available to the engineers, the number of fuel injection systems and their spacing are crucial information which need to be fixed early on in the design phase. Indeed, such choices not only impact the cost and size of the combustor but they also affect the operability of the future engine. One key objective behind these parameters is the ignition time delay needed for the whole combustion chamber to successfully light. To gather knowledge in the ignition process that takes place in real gas turbine engines, current research orient towards the development of experimental facilities that complement high fidelity unsteady numerical simulations. In this context, a multi-injectors experimental set-up located at CORIA (France) is used to validate Large Eddy Simulation (LES) tools developed by CERFACS, IFP-EN and CORIA (France). Preliminary validations against experimental data show that for a given inter-injector distance, LES stationary and ignition transient predictions are very promising and recover the main features found in the experiment. Exit mean and root mean square velocity profiles of the steady flow are in good agreement with measurements obtained for all injectors at multiple axial locations. The simulation of the ignition transient phase well captures global events such as the propagation of the flame front from one injector to its neighbors and the related mechanisms. Improvement is however still needed to recover the proper ignition time of the whole burner.
Throughout 1993 the AIAA Journal will carry selected abstracts on leading research topics from Russian aerospace literature and, as space permits, from similar Japanese literature. The topics will be chosen and the abstracts reviewed for pertinency by AIAA Journal editors. This month features Supersonics from Russia and Large Space Structures from Japan.
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