Abstract
The present paper investigates the influence of film cooling jet inlet boundary condition (IBC) on the large eddy simulation (LES) of film cooling in a model turbine blade with a curved leading edge. Four different IBCs comprising: 1) uniform flow; 2) time independent fully developed turbulent flow and time dependent fully developed turbulent flow perturbed by the vortex method applying two turbulence intensities of 2% and 7% are employed. Results show that accuracy of LES predictions is greatly reliant on coolant jet IBC and case (4) illustrates the best agreement with experiment whilst other cases over-predict the adiabatic effectiveness. Also, film cooling jet IBC not only has a significant influence on flow field vortical structures, but also influences the entrainment and mixing of cold and hot flows. Additionally, the capability of the vortex method for producing a time dependent IBC in leading edge film cooling application is examined and confirmed.
| Original language | English |
|---|---|
| Pages (from-to) | 214-227 |
| Number of pages | 14 |
| Journal | Progress in Computational Fluid Dynamics |
| Volume | 15 |
| Issue number | 4 |
| DOIs | |
| Publication status | Published - 2015 |
Bibliographical note
Publisher Copyright:Copyright © 2015 Inderscience Enterprises Ltd.
Keywords
- Adiabatic effectiveness
- Film cooling
- Inlet boundary condition
- Large eddy simulation
- Leading edge
- LES
- Vortex method
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