Abstract

The present study deals with the assessment of different turbulence models for heated wall jet flow. The velocity field and thermal characteristics for isothermal and uniform heat flux surfaces in the presence of wall jet flow have been predicted using different turbulence models and the results are compared against the experimental data of Wygnanski et al. (1992), Schneider and Goldstein (1994), and AbdulNour et al. (2000). Thirteen different turbulence models are considered for validation, which include the Standard k- (SKE), Realizable k- (RKE), shear stress transport (SST), Sarkar & So (SSA), v 2 -f, Reynolds stress Model (RSM), and Spalart Allmaras (SA) models. Both standard wall function (swf) and enhanced wall treatment (ewt) options available in a commercial CFD solver have been used for near wall treatment for the high Reynolds number models. From the study, it is observed that only a few models could accurately predict the complex flow and thermal features of the heated wall jet. The near wall velocity profile captured using Realizable k- (RKE) with enhanced wall treatment (ewt) shows the best agreement with the experimental data as compared to the other models. Considerable deviation has been observed using SKE with standard wall function (swf) whereas the models of v 2 -f show good prediction of velocity and temperature profiles in the near field region. However, the v 2 -f model is found to deviate from the data in the downstream region where the velocity profiles exhibit similarity. In the prediction of heat transfer coefficient, RSM followed by SA and RKE with ewt, is found to be in closer agreement with the experimental data compared to the rest of the models. The computational time required for RSM is substantially higher than that of the other RANS models. Therefore, in the case of gas turbine combustor, since flow field is much more complex, the RKE with ewt would be the preferred choice over the SA model.

Highlights

  • In recent years aircraft engine gas turbine design is driven by the requirement of low emission and high-efficiency

  • The temperature profiles, thermal boundary layer thicknesss and the heat transfer coefficient predicted by the different turbulence models are compared with that of AbdulNour et al (2000)

  • The computational time required for Reynolds stress Model (RSM) is substantially higher than that of the other Reynolds Averaged Navier Stokes (RANS) models

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Summary

Introduction

In recent years aircraft engine gas turbine design is driven by the requirement of low emission and high-efficiency. A good cooling system must be able to maintain metal temperatures well within the acceptable limits for the most severe engine operating conditions. Wall-jet has been found to be one of the popular methods employed in the cooling of gas turbine combustion chamber liner walls. The performance of most of the two-equation turbulence models in predicting the spread of plane free jets and mixing layers is found to be satisfactory. These models fail to accurately predict near wall flows.

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